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b/Matlab code/Excel Files/FDR010.xlsx new file mode 100755 index 0000000..690b1bd Binary files /dev/null and b/Matlab code/Excel Files/FDR010.xlsx differ diff --git a/Matlab code/Excel Files/FDR012.txt b/Matlab code/Excel Files/FDR012.txt new file mode 100755 index 0000000..7651dd8 --- /dev/null +++ b/Matlab code/Excel Files/FDR012.txt @@ -0,0 +1,7 @@ +0 85 0 CB600155a.dat +2.32 82.73 2.27 CB600165a.dat +6.38 73.67 11.33 CB600175a.dat +14.2 52.13 30.6 CB600175a.dat +28.98 20 45 nasasc0718.dat +34.77 15 50 nasasc0714.dat +80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Matlab code/Excel Files/FDR012.xlsx b/Matlab code/Excel Files/FDR012.xlsx new file mode 100755 index 0000000..e67ecb5 Binary files /dev/null and b/Matlab code/Excel Files/FDR012.xlsx differ diff --git a/Matlab code/Excel Files/FDR013.txt b/Matlab code/Excel Files/FDR013.txt new file mode 100755 index 0000000..4cdef96 --- /dev/null +++ b/Matlab code/Excel Files/FDR013.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0567 +cL0 0.1422 +cMalpha_cruise -0.06 +cM0 -0.1919 + +efficiency 0.8872 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 \ No newline at end of file diff --git a/Matlab code/Excel Files/FDR013b.txt b/Matlab code/Excel Files/FDR013b.txt new file mode 100755 index 0000000..8510d43 --- /dev/null +++ b/Matlab code/Excel Files/FDR013b.txt @@ -0,0 +1,14 @@ +QFLR5 v0.04 Beta + +Wing name : sFD R013 +Wing polar name : T1- 105.0 ft/ s-VLM2- 0. 00ft-Invisc id +Freestream speed : 104 .990 ft/s + +alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP +_________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ +0 0.197841 0.002619 0 0.002619 0 -0.267136 0 0 0 32.001 0.1217 +1 0.254737 0.00402 0 0.00402 0 -0.327464 0 0 0 32.001 0.1159 +2 0.311422 0.005817 0 0.005817 0 -0.387557 0 0 0 32.001 0.1123 +3 0.367837 0.008003 0 0.008003 0 -0.447341 0 0 0 32.001 0.1098 +4 0.423924 0.010575 0 0.010575 0 -0.506744 0 0 0 32.001 0.108 +5 0.479626 0.013523 0 0.013523 0 -0.565693 0 0 0 32.001 0.1067 \ No newline at end of file diff --git a/Matlab code/Excel Files/FDR013b.xlsx b/Matlab code/Excel Files/FDR013b.xlsx new file mode 100755 index 0000000..15e313f Binary files /dev/null and b/Matlab code/Excel Files/FDR013b.xlsx differ diff --git a/Matlab code/Excel Files/FDR020.xlsx b/Matlab code/Excel Files/FDR020.xlsx new file mode 100755 index 0000000..db76f4b Binary files /dev/null and b/Matlab code/Excel Files/FDR020.xlsx differ diff --git a/Matlab code/Excel Files/FDR020points.xlsx b/Matlab code/Excel Files/FDR020points.xlsx new file mode 100755 index 0000000..17fc2c3 Binary files /dev/null and b/Matlab code/Excel Files/FDR020points.xlsx differ diff --git a/Matlab code/Excel Files/PDR001.xlsx b/Matlab code/Excel Files/PDR001.xlsx new file mode 100755 index 0000000..9242435 Binary files /dev/null and b/Matlab code/Excel Files/PDR001.xlsx differ diff --git a/Matlab 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0000000..e53f0de Binary files /dev/null and b/Matlab code/Excel Files/tradeapalooza.xlsx differ diff --git a/Matlab code/Excel Files/xflrdater.xlsx b/Matlab code/Excel Files/xflrdater.xlsx new file mode 100755 index 0000000..76de4f4 Binary files /dev/null and b/Matlab code/Excel Files/xflrdater.xlsx differ diff --git a/Matlab code/Grimace.m b/Matlab code/Grimace.m new file mode 100755 index 0000000..1bb73b1 --- /dev/null +++ b/Matlab code/Grimace.m @@ -0,0 +1,349 @@ +%Grimace +%all alfas in DEGREES! +%by ascorrea, with help from Jacob Huffman +%"filler" variable just makes it easier to switch between Ronald and Grimace + +function Grimace(filler, pranformfile, pranformConstraint) +%LOCATIONS--------------------------------------------------------------] +rootLOCATION='\\ad.uiuc.edu\ae\correa2\Desktop\AE441\AE441 - Home Edition\Matlab code\'; +airfoilLOCATION='\\ad.uiuc.edu\ae\correa2\Desktop\AE441\AE441 - Home Edition\Airfoils'; +pranformLOCATION='\\ad.uiuc.edu\ae\correa2\Desktop\AE441\AE441 - Home Edition\Planforms'; +pranformConstraintLOCATION='\\ad.uiuc.edu\engr\ews\homes\desktop\AE441\AE441 - Home Edition\Planform Constraints'; +paramLOCATION='\\ad.uiuc.edu\engr\ews\homes\desktop\AE441\AE441 - Home Edition\Parameter Files'; +%-----------------------------------------------------------------------] +n=50; +h1=13.33; +h2=10.5; + +cd(pranformLOCATION) +[spans, chords, offsets, airfoil]=textread(pranformfile, '%f %f %f %s'); +cd(pranformConstraintLOCATION) +[spansCONST, chordsCONST, offsetsCONST, heightCONST]=textread(pranformConstraint, '%f %f %f %f'); +cd(rootLOCATION) + +cd(airfoilLOCATION) + +[planformLE planformTE]=plotpranform(spans, chords, offsets, n); +[constraintLE constraintTE]=plotconstraint(spansCONST, chordsCONST, offsetsCONST, n); +plotheight=plotThick(spans, chords, offsets, airfoil, h1, n); +plotheight2=plotThick(spans, chords, offsets, airfoil, h2, n); + + +planformLE=[flipud(planformLE); -planformLE(:,1) planformLE(:,2)]; +planformTE=[flipud(planformTE); -planformTE(:,1) planformTE(:,2)]; +constraintLE=[flipud(constraintLE); -constraintLE(:,1) constraintLE(:,2)]; +constraintTE=[flipud(constraintTE); -constraintTE(:,1) constraintTE(:,2)]; +plotheight=[flipud(plotheight); -plotheight(:,1) plotheight(:,2)]; +plotheight2=[flipud(plotheight2); -plotheight2(:,1) plotheight2(:,2)]; + +clf +hold on +plot(planformLE (:,1), planformLE(:,2),'k','LineWidth',2) +plot(planformTE (:,1), planformTE(:,2),'k','LineWidth',2) +plot(constraintLE (:,1), constraintLE(:,2),'LineWidth',1.5) +plot(constraintTE (:,1), constraintTE(:,2),'LineWidth',1.5) +plot(plotheight(:,1),plotheight(:,2),'r','LineWidth',1) +plot(plotheight2(:,1),plotheight2(:,2),'r--','LineWidth',1) + +axis equal +axis off +hold off +cd(pranformLOCATION) +filename=regexprep(pranformfile, '.plan', 'grim.tiff'); +print ('-dtiff', filename) +cd(rootLOCATION) + +function [plotLE plotTE]=plotpranform(spans, chords, offsets, n) +Chords = findChords(n, chords, spans); + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [plotLE plotTE]=plotconstraint(spans, chords, offsets, n) + +%plot constraint +for i = 1:(size(chords)-1) + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + yplotLE(i,j) = offsets(i+1); + end +end + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) (-yplotLE(i,j)-chords(i+1))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function plotThick=plotThick(spans, chords, offsets, airfoil, h, n) +n=n/10; +Chords = findChords(n, chords, spans); +plotThickLE=zeros(1,2); +plotThickTE=zeros(1,2); + +for i = 1:(size(chords)-1) + for j = 1:n + + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + chordloc=linspace(0, Chords(i,j)); + + for k=1:length(chordloc)-1 + thicknessLE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(k)); + clc + fprintf('%g:%u:%u:%u/%g:%u:%u:%u',h,i,j,k,h,(length(chords)-1),n,(length(chordloc)-1)) + if thicknessLE(k)>=h + plotThickLE=[plotThickLE; xplotLE(i,j) -(chordloc(k)+yplotLE(i,j))]; + break + end + end + + for k=1:length(chordloc)-1 + thicknessTE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(length(chordloc)-k)); + if thicknessTE(k)>=h + plotThickTE=[plotThickTE; xplotLE(i,j) -(chordloc(length(chordloc)-k)+yplotLE(i,j))]; + break + end + end + + end + +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +plotThickLE(1,:)=[]; +plotThickTE(1,:)=[]; +plotThick=[plotThickLE; flipud(plotThickTE)]; +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLoc=h + plotThickLE=[plotThickLE; xplotLE(i,j) -(chordloc(k)+yplotLE(i,j))]; + break + end + end + + for k=1:length(chordloc)-1 + thicknessTE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(length(chordloc)-k)); + if thicknessTE(k)>=h + plotThickTE=[plotThickTE; xplotLE(i,j) -(chordloc(length(chordloc)-k)+yplotLE(i,j))]; + break + end + end + + end + +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +plotThickLE(1,:)=[]; +plotThickTE(1,:)=[]; +plotThick=[plotThickLE; flipud(plotThickTE)]; +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLoc.7 +c_f=c_f*(1-.09*M^2); +end +q=c_f*(swet/sref); +end +function q=findcLalpha(AR, M, clalpha, sweep, sex, sref, doverb) +%ascorrea + +betasquared=1-M^2; +beta=sqrt(betasquared); +eta=clalpha/(2*pi/beta); +numer=2*pi*AR; +denom1=(AR^2*beta^2)/eta^2; +denom2=(tand(sweep)^2/betasquared); +denom=2+sqrt(4+denom1*(1+denom2)); +F=1.07*(1+doverb)^2; + +cLalpha=(numer/denom)*(sex/sref)*F; + +q=cLalpha; + +end +function finddragpolar(cd0, cl_alfa, cL0, e, ar, cd_correction, filename) +alphadeg=[-12:2]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L); +plot(C_d, C_L, '.'); +title(graphname); +xlabel('C_d'); +ylabel('C_L'); +axis([0, .04, -1, 1.5]); +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end +print ('-dtiff', filename) +close(1) +end +function q=findcLrequired(alt, s, v_mach, lift) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +density=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density*v_fps^2; + +q=lift/(q*s); + +end +function q=findalpharequired(cLalpha, cL0, cLrequired) +q=(cLrequired-cL0)/cLalpha; +end +function q=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + q=cd0+cd_i+cd_correction; +end +function [pranformArea WetArea]=WhettedArea(spans, chords, offsets, airfoil, n) +% fileName = 'AirData.mat'; +wingSpan = 1; +% n = 50; + +engineArea=600; +Area = 0; +pranformArea = 0; + +Chords = findChords(n, chords, spans); +for i = 1:(size(chords)-1) + for j = 1:n + Chords(i,j); + dist = wingSpan*(spans(i+1)-spans(i))./n; + Area = Area+findPerim( airfoil{i}, Chords(i,j), wingSpan).*dist; + end +end + +for i = 1:(size(chords)-1) + for j = 1:n + dist = wingSpan*(spans(i+1)-spans(i))./n; + pranformArea = pranformArea+Chords(i,j).*dist; +% fprintf('Chord: %f pranformArea: %f \n', Chords(i,j), pranformArea) + end +end + +Area = Area *2+engineArea; + +WetArea = Area; +pranformArea = pranformArea*2; + +fprintf('Planform Area: %f, Wetted Area: %f \n', pranformArea, WetArea) +end +function Chords = findChords( n, Chord, X ) +for( i = 1:(length(Chord)-1) ) + Xtemp = linspace(X(i),X(i+1),n); + Chords(i,:) = (Chord(i+1)-Chord(i))./(X(i+1)-X(i)).*(Xtemp-X(i))+Chord(i); + +end +end +function peri = findPerim(airFile, chord, span) +peri = 0; +Airfoil = load(airFile); +Airfoil = Airfoil*chord*span; +for i = 1:(size(Airfoil,1)-1) + peri = peri + sqrt((Airfoil(i+1,1)-Airfoil(i,1))^2+(Airfoil(i+1,2)-Airfoil(i,2))^2); +end +end +function [plotLE plotTE]=plotpranform(spans, chords, offsets, airfoil, h, n) + + +Chords = findChords(n, chords, spans); + + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + end +end + +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + end +end + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [plotLE plotTE]=plotconstraint(spans, chords, offsets, n) + +%plot constraint +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + yplotLE(i,j) = offsets(i+1); + end +end + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) (-yplotLE(i,j)-chords(i+1))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function plotThick=plotThick(spans, chords, offsets, airfoil, h, n) + +Chords = findChords(n, chords, spans); + +plotThickLE=zeros(1,2); +plotThickTE=zeros(1,2); +for i=1:size(chords)-1 + for j=size(spans) + chordloc=linspace(0, chords(i)); + for k=1:length(chordloc) + thickness(k)=findthickness(airfoil{i}, chords(i), chordloc(k)); + if thickness(k)>=h + plotThickLE=[plotThickLE; spans(i) -(chordloc(k)+offsets(i))]; + break + end + end + for k=1:length(chordloc)-1 + thicknessLE(k)=findthickness(airfoil{i}, chords(i), chordloc(length(chordloc)-k)); + if thickness(k)>=h + plotThickTE=[plotThickTE; spans(i) -(chordloc(length(chordloc)-k)+offsets(i))]; + break + end + end + end +end + +plotThickLE(1,:)=[]; +plotThickTE(1,:)=[]; +plotThick=[plotThickLE; flipud(plotThickTE)]; + +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + [min_diff, k]=min(abs(AirfoilX)); + [min_diff, xLoc_indu]=min(abs(AirfoilXupper-xLoc)); + [min_diff, xLoc_indl]=min(abs(AirfoilXlower-xLoc)); + + thickness = AirfoilYupper(xLoc_indu)-AirfoilYlower(xLoc_indl); + +end diff --git a/Matlab code/Legacy/MASTER441.m b/Matlab code/Legacy/MASTER441.m new file mode 100755 index 0000000..98bad76 --- /dev/null +++ b/Matlab code/Legacy/MASTER441.m @@ -0,0 +1,411 @@ +%Master 441 Code +%all alfas in DEGREES! +%by ascorrea + +function MASTER441(paramfile, pranformfile, pranformConstraint) +diary +% datafile=input('Input data file: \nNote: You must delete the header +% before using \n:','s'); +%DIRECTORY +%LOCATIONS--------------------------------------------------------------] +% rootLOCATION='\\ad.uiuc.edu\ae\correa2\Desktop\AE441\Matlab code\'; +% airfoilLOCATION='\\ad.uiuc.edu\ae\correa2\Desktop\AE441\Airfoils'; +% pranformLOCATION='\\ad.uiuc.edu\ae\correa2\Desktop\AE441\Planforms'; +% pranformConstraintLOCATION='\\ad.uiuc.edu\engr\ews\homes\desktop\AE441\Pl +% anform Constraints'; +rootLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Matlab code'; +airfoilLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Airfoils'; +pranformLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planforms'; +pranformConstraintLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planform Constraints'; +paramLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Parameter Files'; +%-----------------------------------------------------------------------] + +n=50; +cd(paramLOCATION); +[variablenames, variablevalues]=textread(paramfile, '%s %f'); +cd(pranformLOCATION) +[spans, chords, offsets, airfoil]=textread(pranformfile, '%f %f %f %s'); +cd(pranformConstraintLOCATION) +[spansCONST, chordsCONST, offsetsCONST, heightCONST]=textread(pranformConstraint, '%f %f %f %f'); +cd(airfoilLOCATION) +[sref swet]=WhettedArea(spans, chords, offsets, airfoil, n); +cd(rootLOCATION) + +h1=13.33; +h2=10.5; +h3=9.5; + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end + +wingspan=2*spans(end); +AR=wingspan^2/sref; +%CRUISE------------------------------------------------------------------] +cd0_cruise=findcd0(c_f, M_cruise, sref, swet); +% finddragpolar(cd0_cruise, cLalpha_cruise, cL0, efficiency, AR, cd_correction, 'cruise') +cLreq_cruise=findcLrequired(alt_cruise, sref, M_cruise, weight_cruise); +alphareq_cruise=findalpharequired(cLalpha_cruise, cL0, cLreq_cruise); +cD_cruise=findcD(AR, efficiency, cd0_cruise, cLreq_cruise, cd_correction); +eloverdee_cruise=cLreq_cruise/cD_cruise; +cM_cruise=cMalpha_cruise*alphareq_cruise+cM0; + + +hold on +cd(airfoilLOCATION) + +[planformLE planformTE]=plotpranform(spans, chords, offsets, n); +[constraintLE constraintTE]=plotconstraint(spansCONST, chordsCONST, offsetsCONST, n); +plotheight=plotThick(spans, chords, offsets, airfoil, h1, n); +plotheight2=plotThick(spans, chords, offsets, airfoil, h2, n); +plotheight3=plotThick(spans, chords, offsets, airfoil, h3, n); + +planformLE=[flipud(planformLE); -planformLE(:,1) planformLE(:,2)]; +planformTE=[flipud(planformTE); -planformTE(:,1) planformTE(:,2)]; +constraintLE=[flipud(constraintLE); -constraintLE(:,1) constraintLE(:,2)]; +constraintTE=[flipud(constraintTE); -constraintTE(:,1) constraintTE(:,2)]; +plotheight=[flipud(plotheight); -plotheight(:,1) plotheight(:,2)]; +plotheight2=[flipud(plotheight2); -plotheight2(:,1) plotheight2(:,2)]; +plotheight3=[flipud(plotheight3); -plotheight3(:,1) plotheight3(:,2)]; + + +plot(planformLE (:,1), planformLE(:,2)) +plot(planformTE (:,1), planformTE(:,2)) +plot(constraintLE (:,1), constraintLE(:,2)) +plot(constraintTE (:,1), constraintTE(:,2)) +plot(plotheight(:,1),plotheight(:,2),'r') +plot(plotheight2(:,1),plotheight2(:,2),'r:') +plot(plotheight3(:,1),plotheight3(:,2),'r-.') +axis equal +hold off +fprintf('\n----------Cruise----------\n') +fprintf('alfa: %f, Cd0: %f, CL: %f, CD: %f, CM: %f, L/D: %f \n', alphareq_cruise, cd0_cruise, cLreq_cruise, cD_cruise, cM_cruise, eloverdee_cruise) +cd(rootLOCATION) +end + +function q=findcd0(c_f, M, sref, swet) +if M>.7 +c_f=c_f*(1-.09*M^2); +end +q=c_f*(swet/sref); +end +function q=findcLalpha(AR, M, clalpha, sweep, sex, sref, doverb) +%ascorrea + +betasquared=1-M^2; +beta=sqrt(betasquared); +eta=clalpha/(2*pi/beta); +numer=2*pi*AR; +denom1=(AR^2*beta^2)/eta^2; +denom2=(tand(sweep)^2/betasquared); +denom=2+sqrt(4+denom1*(1+denom2)); +F=1.07*(1+doverb)^2; + +cLalpha=(numer/denom)*(sex/sref)*F; + +q=cLalpha; + +end +function finddragpolar(cd0, cl_alfa, cL0, e, ar, cd_correction, filename) +alphadeg=[-12:2]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L); +plot(C_d, C_L, '.'); +title(graphname); +xlabel('C_d'); +ylabel('C_L'); +axis([0, .04, -1, 1.5]); +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end +print ('-dtiff', filename) +close(1) +end +function q=findcLrequired(alt, s, v_mach, lift) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +density=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density*v_fps^2; + +q=lift/(q*s); + +end +function q=findalpharequired(cLalpha, cL0, cLrequired) +q=(cLrequired-cL0)/cLalpha; +end +function q=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + q=cd0+cd_i+cd_correction; +end +function [pranformArea WetArea]=WhettedArea(spans, chords, ~, airfoil, n) +% fileName = 'AirData.mat'; +wingSpan = 1; +% n = 50; + +engineArea=600; +Area = 0; +pranformArea = 0; + +Chords = findChords(n, chords, spans); +for i = 1:(size(chords)-1) + for j = 1:n + Chords(i,j); + dist = wingSpan*(spans(i+1)-spans(i))./n; + Area = Area+findPerim( airfoil{i}, Chords(i,j), wingSpan).*dist; + end +end + +for i = 1:(size(chords)-1) + for j = 1:n + dist = wingSpan*(spans(i+1)-spans(i))./n; + pranformArea = pranformArea+Chords(i,j).*dist; +% fprintf('Chord: %f pranformArea: %f \n', Chords(i,j), pranformArea) + end +end + +Area = Area *2+engineArea; + +WetArea = Area; +pranformArea = pranformArea*2; + +fprintf('Planform Area: %f, Wetted Area: %f \n', pranformArea, WetArea) +end +function Chords = findChords( n, Chord, X ) +for( i = 1:(length(Chord)-1) ) + Xtemp = linspace(X(i),X(i+1),n); + Chords(i,:) = (Chord(i+1)-Chord(i))./(X(i+1)-X(i)).*(Xtemp-X(i))+Chord(i); + +end +end +function peri = findPerim(airFile, chord, span) +peri = 0; +Airfoil = load(airFile); +Airfoil = Airfoil*chord*span; +for i = 1:(size(Airfoil,1)-1) + peri = peri + sqrt((Airfoil(i+1,1)-Airfoil(i,1))^2+(Airfoil(i+1,2)-Airfoil(i,2))^2); +end +end +function [plotLE plotTE]=plotpranform(spans, chords, offsets, n) +Chords = findChords(n, chords, spans); + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [plotLE plotTE]=plotconstraint(spans, chords, offsets, n) + +%plot constraint +for i = 1:(size(chords)-1) + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + yplotLE(i,j) = offsets(i+1); + end +end + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) (-yplotLE(i,j)-chords(i+1))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function plotThick=plotThick(spans, chords, offsets, airfoil, h, n) +n=n/25; +Chords = findChords(n, chords, spans); +plotThickLE=zeros(1,2); +plotThickTE=zeros(1,2); + +for i = 1:(size(chords)-1) + for j = 1:n + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + chordloc=linspace(0, Chords(i,j)); + + for k=1:length(chordloc)-1 + thickness(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(k)); + if thickness(k)>=h + plotThickLE=[plotThickLE; xplotLE(i,j) -(chordloc(k)+yplotLE(i,j))]; + break + end + end + + for k=1:length(chordloc)-1 + thicknessLE(k)=findthickness(airfoil{i}, chords(i), chordloc(length(chordloc)-k)); + if thickness(k)>=h + plotThickTE=[plotThickTE; xplotLE(i,j) -(chordloc(length(chordloc)-k)+yplotLE(i,j))]; + break + end + end + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +plotThickLE(1,:)=[]; +plotThickTE(1,:)=[]; +plotThick=[plotThickLE; flipud(plotThickTE)]; +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLoc 30 deg + +c_L=input('Input c_L: '); +ar=input('Input aspect ratio: '); +sweep_LE=input('Input leading edge sweep (deg): '); + +e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + +cd_i=c_L^2/(pi*ar*e); + +fprintf('cd_i: %f \n', cd_i); diff --git a/Matlab code/Legacy/omkarshitty.m b/Matlab code/Legacy/omkarshitty.m new file mode 100755 index 0000000..25d56be --- /dev/null +++ b/Matlab code/Legacy/omkarshitty.m @@ -0,0 +1,35 @@ +%omkar + +nu_ft2ps = 1.764e-4; +rho_slugpft3 = 0.0020451; +c_ft = 10; +xtr_ft = .2*c_ft; + +ft_2_in = 12; +Vinf_fps = 198; +q = 0.5 * rho_slugpft3 * (Vinf_fps^2); +Re_xtr = Vinf_fps * xtr_ft / nu_ft2ps; +delta_xtr_ft=( 5.2 * xtr_ft )/(Re_xtr)^0.5; +delta_l_ft = ((delta_xtr_ft*((Vinf_fps)^0.2))/(0.37*((nu_ft2ps)^0.2)))^(1/0.8); +lt_ft = c_ft - xtr_ft + delta_l_ft; +Re_lt = Vinf_fps * lt_ft / nu_ft2ps; +delta_ft = 0.37 * lt_ft /(Re_lt)^0.2 + + +% for k = 1:100 +% if (k <= 100*lam) +% Re_x = v_fps * x(k) / dynvisc; +% delta_x=( 5.2 * x(k) )/(Re_x)^0.5; +% wake(j,k)= delta_x; +% else %if turbulent +% x_tr=x(100*lam); +% Re_xtr = v_fps * x_tr / dynvisc; +% delta_xtr=( 5.2 * x_tr )/(Re_xtr)^0.5; +% delta_l = ((delta_xtr*((v_fps)^0.2))/(0.37*((dynvisc)^0.2)))^(1/0.8); +% lt = x(k) - x_tr + delta_l; +% Re_lt = v_fps * lt / dynvisc; +% delta = 0.37 * lt /(Re_lt)^0.2; +% wake(j,k) = delta; +% end +% +% end \ No newline at end of file diff --git a/Matlab code/Legacy/penis.m b/Matlab code/Legacy/penis.m new file mode 100755 index 0000000..7249326 --- /dev/null +++ b/Matlab code/Legacy/penis.m @@ -0,0 +1,14 @@ +function penis + +while true + for k = logspace(-.1,-3,15) + for j = 1:25 + for i = 1:j + fprintf(' '); + end + fprintf('8=====>\n') + pause(k) + clc + end + end +end \ No newline at end of file diff --git a/Matlab code/Ronald.m b/Matlab code/Ronald.m new file mode 100755 index 0000000..76d54a9 --- /dev/null +++ b/Matlab code/Ronald.m @@ -0,0 +1,520 @@ +%Ronald +%all alfas in DEGREES! +%by ascorrea, with help from Jacob Huffman +%"filler" variable just makes it easier to switch between Ronald and Grimace + +function Ronald(paramfile, pranformfile, filler) + +%DIRECTORY LOCATIONS--------------------------------------------------------------] +rootLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Matlab Code'; +airfoilLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Airfoils'; +pranformLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planforms'; +pranformConstraintLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planform Constraints'; +paramLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Parameter Files'; +outputsLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/superGrimace Outputs'; +%-----------------------------------------------------------------------] + +n=50; +cd(paramLOCATION); +[variablenames, variablevalues]=textread(paramfile, '%s %f'); +cd(pranformLOCATION) +[spans, chords, offsets, airfoil]=textread(pranformfile, '%f %f %f %s'); +cd(airfoilLOCATION) +[sref swet]=WhettedArea(spans, chords, offsets, airfoil, n); + + + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end + +Dragredux_BLI=(1-Dragredux_BLI/100); + +wingspan=2*spans(end); +AR=wingspan^2/sref; +wakeplot=findwake(airfoil, chords, spans, offsets, n, alt_cruise, M_cruise, laminarflow_cruise, fuse_width); + +%TAKEOFF------------------------------------------------------------------] +% cd0_to=findcd0(c_f, M_to, sref, swet); +cd0_to=findcd0(spans, chords, offsets, airfoil, n, laminarflow_to, alt_to, M_to, sref, c_f, D_engine, cd_landinggear, sfront_landinggear, fuse_width); +% finddragpolar(cd0_to, cLalpha_to, cL0, efficiency_to, AR, cd_correction, 'Takeoff') +% cLreq_to=findcLrequired(alt_to, sref, M_to, weight_to); +cLreq_to=.48; +alphareq_to=findalpharequired(cLalpha, cL0, cLreq_to); +cD_to=findcD(AR, efficiency_to, cd0_to, cLreq_to, cd_correction); +eloverdee_to=cLreq_to/cD_to; +cM_to=cMalpha*alphareq_to+cM0; +q_to=finddynpress(alt_to, M_to); +cD_to=cD_to*Dragredux_BLI; +cd0_to=cd0_to*Dragredux_BLI; +D_to=cD_to*q_to*sref; + +%CRUISE------------------------------------------------------------------] +cd0_cruise=findcd0(spans, chords, offsets, airfoil, n, laminarflow_cruise, alt_cruise, M_cruise, sref, c_f, D_engine, 0, 0, fuse_width); +% finddragpolar(cd0_cruise, cLalpha, cL0, efficiency_cruise, AR, cd_correction, 'Cruise') +cLreq_cruise=findcLrequired(alt_cruise, sref, M_cruise, weight_cruise); +alphareq_cruise=findalpharequired(cLalpha, cL0, cLreq_cruise); +cD_cruise=findcD(AR, efficiency_cruise, cd0_cruise, cLreq_cruise, cd_correction); +cM_cruise=cMalpha*alphareq_cruise+cM0; +q_cruise=finddynpress(alt_cruise, M_cruise); +cD_cruise=cD_cruise*Dragredux_BLI; +cd0_cruise=cd0_cruise*Dragredux_BLI; +D_cruise=cD_cruise*q_cruise*sref; +eloverdee_cruise=cLreq_cruise/cD_cruise; + +%LOITER------------------------------------------------------------------] +cd0_loiter=findcd0(spans, chords, offsets, airfoil, n, laminarflow_loiter, alt_loiter, M_loiter, sref, c_f, D_engine, 0, 0, fuse_width); +% finddragpolar(cd0_loiter, cLalpha_loiter, cL0, efficiency_loiter, AR, cd_correction, 'Loiter') +cLreq_loiter=findcLrequired(alt_loiter, sref, M_loiter, weight_loiter); +alphareq_loiter=findalpharequired(cLalpha, cL0, cLreq_loiter); +cD_loiter=findcD(AR, efficiency_loiter, cd0_loiter, cLreq_loiter, cd_correction); +cM_loiter=cMalpha*alphareq_loiter+cM0; +q_loiter=finddynpress(alt_loiter, M_loiter); +cD_loiter=cD_loiter*Dragredux_BLI; +cd0_loiter=cd0_loiter*Dragredux_BLI; +D_loiter=cD_loiter*q_loiter*sref; +eloverdee_loiter=cLreq_loiter/cD_loiter; + +%LANDING------------------------------------------------------------------] +cd0_landing=findcd0(spans, chords, offsets, airfoil, n, laminarflow_landing, alt_landing, M_landing, sref, c_f, D_engine, cd_landinggear, sfront_landinggear, fuse_width); +% finddragpolar(cd0_landing, cLalpha_landing, cL0, efficiency_landing, AR, cd_correction, 'Landing') +% cLreq_landing=findcLrequired(alt_landing, sref, M_landing, weight_landing); +cLreq_landing=.401; +alphareq_landing=findalpharequired(cLalpha, cL0, cLreq_landing); +cD_landing=findcD(AR, efficiency_landing, cd0_landing, cLreq_landing, cd_correction); +cM_landing=cMalpha*alphareq_landing+cM0; +q_landing=finddynpress(alt_landing, M_landing); +cD_landing=cD_landing*Dragredux_BLI; +cd0_landing=cd0_landing*Dragredux_BLI; +D_landing=cD_landing*q_landing*sref; +eloverdee_landing=cLreq_landing/cD_landing; + +cd(pranformLOCATION) +filenameplan=regexprep(pranformfile, '.plan', 'ronaldplus.tiff'); +filenameoutput=regexprep(pranformfile, '.plan', 'ronaldplus.txt'); +plottitle=regexprep(pranformfile, '.plan', ''); + +fid = fopen(filenameoutput, 'w'); +fprintf(plottitle); +fprintf('---------------------------------------------------\n'); +fprintf(fid, plottitle); +fprintf(fid,'---------------------------------------------------\n'); + +fprintf('Wingspan: %f, AR: %f, Planform Area: %f, Wetted Area: %f \n', wingspan, AR, sref, swet); +fprintf(fid, 'Wingspan: %f, AR: %f, Planform Area: %f, Wetted Area: %f \n', wingspan, AR, sref, swet); + +fprintf('\n----------Takeoff--------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_to, cd0_to, cLreq_to, cD_to, D_to, cM_to, eloverdee_to); +fprintf(fid, '\n----------Takeoff--------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_to, cd0_to, cLreq_to, cD_to, D_to, cM_to, eloverdee_to); + +fprintf('\n----------Cruise---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_cruise, cd0_cruise, cLreq_cruise, cD_cruise, D_cruise, cM_cruise, eloverdee_cruise); +fprintf(fid, '\n----------Cruise---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_cruise, cd0_cruise, cLreq_cruise, cD_cruise, D_cruise, cM_cruise, eloverdee_cruise); + +fprintf('\n----------Loiter---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_loiter, cd0_loiter, cLreq_loiter, cD_loiter, D_loiter, cM_loiter, eloverdee_loiter); +fprintf(fid, '\n----------Loiter---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_loiter, cd0_loiter, cLreq_loiter, cD_loiter, D_loiter, cM_loiter, eloverdee_loiter); + +fprintf('\n----------Landing--------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_landing, cd0_landing, cLreq_landing, cD_landing, D_landing, cM_landing, eloverdee_landing); +fprintf(fid, '\n----------Landing--------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f, CM: %f, L/D: %f \n', alphareq_landing, cd0_landing, cLreq_landing, cD_landing, D_landing, cM_landing, eloverdee_landing); + + +fclose(fid); +cd(rootLOCATION) +end + +% function cd0=findcd0(c_f, M, sref, swet) +% if M>.7 +% c_f=c_f*(1-.09*M^2); +% end +% cd0=c_f*(swet/sref); +% end +function cd0=findcd0(spans, chords, offsets, airfoil, n, laminarflow, alt, v_mach, sref, c_f, D_engine, cd_lg, Sfront_lg, width) +wingSpan = 1; +% n = 50; +width=width/2; + +[q v_fps dynvisc]=findconstants(alt, v_mach); +drag=0; +drag_fuse=0; +drag_wing=0; + +Chords = findChords(n, chords, spans); +for i = 1:(size(chords)-1) + for j = 1:n + dist = wingSpan*(spans(i+1)-spans(i))./n; + chordloc=linspace(0, Chords(i,j)); + delta_x = Chords(i,j)/100; + + if spans(i)>width + for k = 1:100 + x(k)= k * Chords(i,j)/100; + Re_x(k)= v_fps * x(k)/dynvisc; + if (k <= 100*laminarflow ) + cf_x(k) = 0.664 /(sqrt(Re_x(k))); + else % Turbulent + cf_x(k) = 0.455 /(log(0.06 * Re_x(k))^2); + end + xcf_x(k)=x(k)*cf_x(k); + end + t = trapz(cf_x); + Cf = 2 * delta_x * t /Chords(i,j); + drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist; + drag_wing=drag_wing+drag_section; + else + for k = 1:100 + x(k)= k * Chords(i,j)/100; + Re_x(k)= v_fps * x(k)/dynvisc; + if (k <= 100*laminarflow -10) + cf_x(k) = 0.664 /(sqrt(Re_x(k))); + else % Turbulent + cf_x(k) = 0.455 /(log(0.06 * Re_x(k))^2); + end + xcf_x(k)=x(k)*cf_x(k); + end + t = trapz(cf_x); + Cf = 2 * delta_x * t /Chords(i,j); + drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist; + drag_fuse=drag_fuse+drag_section; + end + t = trapz(cf_x); + Cf = 2 * delta_x * t /Chords(i,j); + drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist; + drag=drag+drag_section; + + end +end + +if v_mach>.7 +c_f=c_f*(1-.09*v_mach)^2; +end +% cd0engine=c_f*(s_engine/sref); +D_lg=Sfront_lg*q*cd_lg; +D_wing=drag_wing*2; +D_fuse=drag_fuse*2; +drag_tot=D_wing+D_engine+D_lg+D_fuse; +cd0=drag_tot/(q*sref); +cD_lg=D_lg/(q*sref); +cD_engine=D_engine/(q*sref); +cD_wing=D_wing/(q*sref); +cD_fuse=D_fuse/(q*sref); +end +function finddragpolar(cd0, cl_alfa, cL0, e, ar, cd_correction, filename) +alphadeg=[-12:10]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +grid on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L, 'k', 'LineWidth', 2); +plot(C_d, C_L, 'k.'); +title(graphname); +xlabel('C_d', 'FontSize', 16); +ylabel('C_L', 'FontSize', 16); +axis([0, .02, -.3, .4]); +set(gca, 'FontSize',16) + +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end + +print ('-dtiff', filename) +grid off +close(1) +end +function q=finddynpress(alt, v_mach) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +%slpcuft: clugs ber cubic foot +density_slpcuft=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density_slpcuft*v_fps^2; +end +function [q v_fps dynvisc]=findconstants(alt, v_mach) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +%slpcuft: clugs ber cubic foot +density_slpcuft=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=finddynpress(alt, v_mach); + +S = 110.4; +beta = 1.458e-6; +temp_k=[(temp-32) / (1.8)] + 273 ; +viscosity_pascalseconds = (beta*temp_k^(1.5))/(temp_k+S); +%kgpmcu:kilograms per meter cubed +%msqpse:meters squared per second +%sqftpsec:square feet per second +density_kgpmcu=density_slpcuft*515.4; +dynamic_viscosity_msqpsec=viscosity_pascalseconds/density_kgpmcu; +dynamic_viscosity_sqftpsec=dynamic_viscosity_msqpsec*10.76; +dynvisc=dynamic_viscosity_sqftpsec; +density=density_slpcuft; +end +function cLreq=findcLrequired(alt, s, v_mach, lift) +q=finddynpress(alt, v_mach); + +cLreq=lift/(q*s); + +end +function alpha=findalpharequired(cLalpha, cL0, cLrequired) +alpha=(cLrequired-cL0)/cLalpha; +end +function cD=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + cD=cd0+cd_i+cd_correction; +end +function [pranformArea WetArea]=WhettedArea(spans, chords, offsets, airfoil, n) +% fileName = 'AirData.mat'; +wingSpan = 1; +% n = 50; + +engineArea=0; +Area = 0; +pranformArea = 0; + +Chords = findChords(n, chords, spans); +for i = 1:(size(chords)-1) + for j = 1:n + Chords(i,j); + dist = wingSpan*(spans(i+1)-spans(i))./n; + Area = Area+findPerim( airfoil{i}, Chords(i,j), wingSpan).*dist; + end +end + +for i = 1:(size(chords)-1) + for j = 1:n + dist = wingSpan*(spans(i+1)-spans(i))./n; + pranformArea = pranformArea+Chords(i,j).*dist; +% fprintf('Chord: %f pranformArea: %f \n', Chords(i,j), pranformArea) + end +end + +Area = Area *2+engineArea; + +WetArea = Area; +pranformArea = pranformArea*2; +end +function Chords = findChords( n, Chord, X ) +for( i = 1:(length(Chord)-1) ) + Xtemp = linspace(X(i),X(i+1),n); + Chords(i,:) = (Chord(i+1)-Chord(i))./(X(i+1)-X(i)).*(Xtemp-X(i))+Chord(i); + +end +end +function peri = findPerim(airFile, chord, span) +peri = 0; +Airfoil = load(airFile); +Airfoil = Airfoil*chord*span; +for i = 1:(size(Airfoil,1)-1) + peri = peri + sqrt((Airfoil(i+1,1)-Airfoil(i,1))^2+(Airfoil(i+1,2)-Airfoil(i,2))^2); +end +end +function [plotLE plotTE]=plotpranform(spans, chords, offsets, n) +Chords = findChords(n, chords, spans); + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [wakeplot]=findwake(airfoil, chords, spans, offsets, n, alt, v_mach, laminarflow, width) +[q v_fps dynvisc]=findconstants(alt, v_mach); +Chords = findChords(n, chords, spans); +wakeplot=zeros(100,1); +wakeplotX=zeros(100,1); +wakeplotY=zeros(100,1); +width=width/2; +% for i = 1:(size(chords)-1) +for i=1:1:(size(chords)-1) + for j = 1:n +% wakecoord(j,:)=linspace(0, Chords(i,j), n); +dist = (spans(i+1)-spans(i))./n; +y(j)=spans(i)+j*dist; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + if spans(i)>width + lam=laminarflow; + else + lam=laminarflow-.15; + end + x=linspace(0, Chords(i,j)); + for k = 1:length(x) + if (k <= 100*lam) + delta_x=( 5.2 * x(k) )*(v_fps*x(k)/dynvisc)^-0.5; + wake(k,j)= delta_x; + else %if turbulent + x_tr=x(100*lam); + Re_xtr = v_fps * x_tr / dynvisc; + delta_xtr=(5.2*x_tr)*(v_fps*x(k)/dynvisc)^-(0.5); + delta_l = ((delta_xtr*((v_fps)^0.2))/(0.37*((dynvisc)^0.2)))^(1/0.8); + lt = x(k) - x_tr + delta_l; + Re_lt = v_fps * lt / dynvisc; + delta = 0.37 * lt /(Re_lt)^0.2; + wake(k,j) = delta; + end + +wakeX(k,j)=x(k)+yplotLE(i,j); +wakeY(k,j)=y(j); + end + + for k = 1:100 + + wakeX(k,j)=x(k)+yplotLE(i,j); + wakeY(k,j)=y(j); + end + + + +wakeplot=[wakeplot, wake]; +wakeplotX=[wakeplotX, wakeX]; +wakeplotY=[wakeplotY, wakeY]; + end + +end +wakeplot(:,1)=[ ]; +wakeplotX(:,1)=[ ]; +wakeplotY(:,1)=[ ]; +wakeplot(1,:)=[0]; +flipud(wakeplot); +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLoc.7 +% c_f=c_f*(1-.09*M^2); +% end +% cd0=c_f*(swet/sref); +% end +function [cd0 D_wing D_fuse]=findcd0(spans, chords, offsets, airfoil, n, laminarflow, alt, v_mach, sref, c_f, D_engine, cd_lg, Sfront_lg, width) +wingSpan = 1; +% n = 50; +width=width/2; + +[q v_fps dynvisc]=findconstants(alt, v_mach); +drag=0; +drag_fuse=0; +drag_wing=0; + +Chords = findChords(n, chords, spans); +for i = 1:(size(chords)-1) + for j = 1:n + dist = wingSpan*(spans(i+1)-spans(i))./n; + chordloc=linspace(0, Chords(i,j)); + delta_x = Chords(i,j)/100; + + if spans(i)>width + for k = 1:100 + x(k)= k * Chords(i,j)/100; + Re_x(k)= v_fps * x(k)/dynvisc; + if (k <= 100*laminarflow ) + cf_x(k) = 0.664 /(sqrt(Re_x(k))); + else % Turbulent + cf_x(k) = 0.455 /(log(0.06 * Re_x(k))^2); + end + xcf_x(k)=x(k)*cf_x(k); + end + t = trapz(cf_x); + Cf = 2 * delta_x * t /Chords(i,j); + drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist; + drag_wing=drag_wing+drag_section; + else + for k = 1:100 + x(k)= k * Chords(i,j)/100; + Re_x(k)= v_fps * x(k)/dynvisc; + if (k <= 100*laminarflow -10) + cf_x(k) = 0.664 /(sqrt(Re_x(k))); + else % Turbulent + cf_x(k) = 0.455 /(log(0.06 * Re_x(k))^2); + end + xcf_x(k)=x(k)*cf_x(k); + end + t = trapz(cf_x); + Cf = 2 * delta_x * t /Chords(i,j); + drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist; + drag_fuse=drag_fuse+drag_section; + end + t = trapz(cf_x); + Cf = 2 * delta_x * t /Chords(i,j); + drag_section = q*Cf*findPerim(airfoil{i}, Chords(i,j), wingSpan).*dist; + drag=drag+drag_section; + + end +end + +if v_mach>.7 +c_f=c_f*(1-.09*v_mach)^2; +end +% cd0engine=c_f*(s_engine/sref); +D_lg=Sfront_lg*q*cd_lg; +D_wing=drag_wing*2; +D_fuse=drag_fuse*2; +drag_tot=D_wing+D_engine+D_lg+D_fuse; +cd0=drag_tot/(q*sref); +cD_lg=D_lg/(q*sref); +cD_engine=D_engine/(q*sref); +cD_wing=D_wing/(q*sref); +cD_fuse=D_fuse/(q*sref); +end +function finddragpolar(cd0, cl_alfa, cL0, e, ar, cd_correction, filename) +alphadeg=[-12:10]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +grid on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L, 'k', 'LineWidth', 2); +plot(C_d, C_L, 'k.'); +title(graphname); +xlabel('C_d', 'FontSize', 16); +ylabel('C_L', 'FontSize', 16); +axis([0, .02, -.3, .4]); +set(gca, 'FontSize',16) + +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end + +print ('-dtiff', filename) +grid off +close(1) +end +function q=finddynpress(alt, v_mach) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +%slpcuft: clugs ber cubic foot +density_slpcuft=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density_slpcuft*v_fps^2; +end +function [q v_fps dynvisc]=findconstants(alt, v_mach) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +%slpcuft: clugs ber cubic foot +density_slpcuft=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=finddynpress(alt, v_mach); + +S = 110.4; +beta = 1.458e-6; +temp_k=[(temp-32) / (1.8)] + 273 ; +viscosity_pascalseconds = (beta*temp_k^(1.5))/(temp_k+S); +%kgpmcu:kilograms per meter cubed +%msqpse:meters squared per second +%sqftpsec:square feet per second +density_kgpmcu=density_slpcuft*515.4; +dynamic_viscosity_msqpsec=viscosity_pascalseconds/density_kgpmcu; +dynamic_viscosity_sqftpsec=dynamic_viscosity_msqpsec*10.76; +dynvisc=dynamic_viscosity_sqftpsec; +density=density_slpcuft; +end +function cLreq=findcLrequired(alt, s, v_mach, lift) +q=finddynpress(alt, v_mach); + +cLreq=lift/(q*s); + +end +function alpha=findalpharequired(cLalpha, cL0, cLrequired) +alpha=(cLrequired-cL0)/cLalpha; +end +function cD=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + cD=cd0+cd_i+cd_correction; +end +function [pranformArea WetArea]=WhettedArea(spans, chords, offsets, airfoil, n) +% fileName = 'AirData.mat'; +wingSpan = 1; +% n = 50; + +engineArea=0; +Area = 0; +pranformArea = 0; + +Chords = findChords(n, chords, spans); +for i = 1:(size(chords)-1) + for j = 1:n + Chords(i,j); + dist = wingSpan*(spans(i+1)-spans(i))./n; + Area = Area+findPerim( airfoil{i}, Chords(i,j), wingSpan).*dist; + end +end + +for i = 1:(size(chords)-1) + for j = 1:n + dist = wingSpan*(spans(i+1)-spans(i))./n; + pranformArea = pranformArea+Chords(i,j).*dist; +% fprintf('Chord: %f pranformArea: %f \n', Chords(i,j), pranformArea) + end +end + +Area = Area *2+engineArea; + +WetArea = Area; +pranformArea = pranformArea*2; +end +function Chords = findChords( n, Chord, X ) +for( i = 1:(length(Chord)-1) ) + Xtemp = linspace(X(i),X(i+1),n); + Chords(i,:) = (Chord(i+1)-Chord(i))./(X(i+1)-X(i)).*(Xtemp-X(i))+Chord(i); + +end +end +function peri = findPerim(airFile, chord, span) +peri = 0; +Airfoil = load(airFile); +Airfoil = Airfoil*chord*span; +for i = 1:(size(Airfoil,1)-1) + peri = peri + sqrt((Airfoil(i+1,1)-Airfoil(i,1))^2+(Airfoil(i+1,2)-Airfoil(i,2))^2); +end +end +function [plotLE plotTE]=plotpranform(spans, chords, offsets, n) +Chords = findChords(n, chords, spans); + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [wakeplot]=findwake(airfoil, chords, spans, offsets, n, alt, v_mach, laminarflow, width) +[q v_fps dynvisc]=findconstants(alt, v_mach); +Chords = findChords(n, chords, spans); +wakeplot=zeros(100,1); +wakeplotX=zeros(100,1); +wakeplotY=zeros(100,1); +width=width/2; +% for i = 1:(size(chords)-1) +for i=1:1:(size(chords)-1) + for j = 1:n +% wakecoord(j,:)=linspace(0, Chords(i,j), n); +dist = (spans(i+1)-spans(i))./n; +y(j)=spans(i)+j*dist; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + if spans(i)>width + lam=laminarflow; + else + lam=laminarflow-.15; + end + x=linspace(0, Chords(i,j)); + for k = 1:length(x) + if (k <= 100*lam) + delta_x=( 5.2 * x(k) )*(v_fps*x(k)/dynvisc)^-0.5; + wake(k,j)= delta_x; + else %if turbulent + x_tr=x(100*lam); + Re_xtr = v_fps * x_tr / dynvisc; + delta_xtr=(5.2*x_tr)*(v_fps*x(k)/dynvisc)^-(0.5); + delta_l = ((delta_xtr*((v_fps)^0.2))/(0.37*((dynvisc)^0.2)))^(1/0.8); + lt = x(k) - x_tr + delta_l; + Re_lt = v_fps * lt / dynvisc; + delta = 0.37 * lt /(Re_lt)^0.2; + wake(k,j) = delta; + end + +wakeX(k,j)=x(k)+yplotLE(i,j); +wakeY(k,j)=y(j); + end + + for k = 1:100 + + wakeX(k,j)=x(k)+yplotLE(i,j); + wakeY(k,j)=y(j); + end + + + +wakeplot=[wakeplot, wake]; +wakeplotX=[wakeplotX, wakeX]; +wakeplotY=[wakeplotY, wakeY]; + end + +end +wakeplot(:,1)=[ ]; +wakeplotX(:,1)=[ ]; +wakeplotY(:,1)=[ ]; +wakeplot(1,:)=[0]; +flipud(wakeplot); +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLoctmax-x1) + tsave=t; + t=tmax-x1; + flag=2; + +elseif (t0); +thetaTE=reversefit(P,t/2,theta(roots(1))); +rTE=ppval(P,thetaTE); +xTE=rTE*cos(thetaTE); +thetaLE=reversefit(P,t/2,theta(roots(2))); +rLE=ppval(P,thetaLE); +xLE=rLE*cos(thetaLE); +l=abs(xTE-xLE); +AR=l/t; + +if flag==1 + x3=2*x1; + y1=AR; + y2=1.1*AR; + a = (y1-y2)/(-2*x3*x1+x1^2); + b=(y1-a*x1^2-y2)/x1; + AR=a*tsave^2+b*tsave+y2; +elseif flag==2 + x3=tmax-x1*.001; + x2=tmax; + x1=tmax-2*x1; + a=-AR/((x2^2-x3^2)-2*x1*(x2-x3)); + b=-2*a*x1; + c=-a*x2^2-b*x2; + AR=a*tsave^2+b*tsave+c; +end; diff --git a/Matlab code/strut/CB3.dat b/Matlab code/strut/CB3.dat new file mode 100755 index 0000000..5357b11 --- /dev/null +++ b/Matlab code/strut/CB3.dat @@ -0,0 +1,60 @@ +Centerbody 3 + 0.92743 0.03097 + 0.88580 0.03617 + 0.83259 0.04000 + 0.77100 0.04266 + 0.70420 0.04437 + 0.63540 0.04534 + 0.56776 0.04578 + 0.50371 0.04585 + 0.44392 0.04568 + 0.38886 0.04536 + 0.33898 0.04499 + 0.29474 0.04467 + 0.25657 0.04450 + 0.22425 0.04448 + 0.19666 0.04448 + 0.17264 0.04438 + 0.15102 0.04404 + 0.13063 0.04334 + 0.11039 0.04214 + 0.09021 0.04042 + 0.07079 0.03824 + 0.05285 0.03564 + 0.03713 0.03269 + 0.02434 0.02944 + 0.01508 0.02594 + 0.00899 0.02216 + 0.00531 0.01807 + 0.00325 0.01363 + 0.00203 0.00880 + 0.00088 0.00354 + 0.00084 -0.00546 + 0.00269 -0.01211 + 0.00680 -0.01962 + 0.01437 -0.02765 + 0.02663 -0.03587 + 0.04482 -0.04397 + 0.07014 -0.05160 + 0.10364 -0.05845 + 0.14471 -0.06435 + 0.19192 -0.06920 + 0.24380 -0.07289 + 0.29892 -0.07532 + 0.35581 -0.07639 + 0.41302 -0.07600 + 0.46913 -0.07405 + 0.52309 -0.07058 + 0.57428 -0.06580 + 0.62208 -0.05990 + 0.66587 -0.05307 + 0.70504 -0.04551 + 0.73898 -0.03742 + 0.76707 -0.02899 + 0.78959 -0.02039 + 0.80857 -0.01167 + 0.82619 -0.00288 + 0.84469 0.00592 + 0.86625 0.01468 + 0.89310 0.02334 + 0.92743 0.03186 diff --git a/Matlab code/strut/CB4.dat b/Matlab code/strut/CB4.dat new file mode 100755 index 0000000..ac5254d --- /dev/null +++ b/Matlab code/strut/CB4.dat @@ -0,0 +1,60 @@ +Centerbody 4 + 0.91334 0.02171 + 0.87802 0.03287 + 0.82202 0.04154 + 0.75161 0.04805 + 0.67304 0.05272 + 0.59260 0.05591 + 0.51655 0.05793 + 0.44911 0.05907 + 0.39005 0.05946 + 0.33849 0.05924 + 0.29356 0.05851 + 0.25442 0.05742 + 0.22019 0.05607 + 0.19013 0.05455 + 0.16366 0.05285 + 0.14022 0.05098 + 0.11921 0.04894 + 0.10008 0.04672 + 0.08226 0.04433 + 0.06558 0.04169 + 0.05009 0.03871 + 0.03589 0.03528 + 0.02306 0.03128 + 0.01169 0.02660 + 0.00186 0.02118 +-0.00621 0.01519 +-0.01228 0.00894 +-0.01609 0.00272 +-0.01740 -0.00318 +-0.01595 -0.00844 +-0.01403 -0.01488 +-0.01170 -0.01993 +-0.00658 -0.02531 + 0.00278 -0.03084 + 0.01782 -0.03636 + 0.03997 -0.04172 + 0.07067 -0.04676 + 0.11111 -0.05130 + 0.16022 -0.05517 + 0.21577 -0.05819 + 0.27553 -0.06016 + 0.33725 -0.06092 + 0.39870 -0.06026 + 0.45764 -0.05800 + 0.51190 -0.05397 + 0.56072 -0.04828 + 0.60476 -0.04132 + 0.64472 -0.03348 + 0.68132 -0.02516 + 0.71528 -0.01676 + 0.74732 -0.00867 + 0.77814 -0.00131 + 0.80793 0.00506 + 0.83590 0.01040 + 0.86111 0.01467 + 0.88263 0.01788 + 0.89954 0.01999 + 0.91093 0.02099 + 0.91585 0.02087 diff --git a/Matlab code/strut/CB40015.dat b/Matlab code/strut/CB40015.dat new file mode 100755 index 0000000..624f576 --- /dev/null +++ b/Matlab code/strut/CB40015.dat @@ -0,0 +1,60 @@ +Centerbody 4 + 0.913338 0.021800 + 0.877970 0.034797 + 0.821913 0.045691 + 0.751433 0.054894 + 0.672786 0.062540 + 0.592283 0.068148 + 0.516194 0.071685 + 0.448734 0.073592 + 0.389666 0.074289 + 0.338105 0.074109 + 0.293179 0.073245 + 0.254045 0.071912 + 0.219823 0.070247 + 0.189772 0.068366 + 0.163313 0.066266 + 0.139884 0.063965 + 0.118886 0.061463 + 0.099769 0.058747 + 0.081963 0.055821 + 0.065298 0.052587 + 0.049825 0.048941 + 0.035645 0.044756 + 0.022837 0.039891 + 0.011493 0.034215 + 0.001693 0.027642 + -0.006343 0.020334 + -0.012373 0.012545 + -0.016127 0.004160 + -0.017398 -0.003265 + -0.015915 -0.009781 + -0.013964 -0.017422 + -0.011608 -0.023477 + -0.006454 -0.030168 + 0.002946 -0.037244 + 0.018028 -0.044397 + 0.040218 -0.051317 + 0.070955 -0.057764 + 0.111427 -0.063556 + 0.160565 -0.068479 + 0.216135 -0.072286 + 0.275908 -0.074779 + 0.337635 -0.075783 + 0.399083 -0.075073 + 0.458015 -0.072478 + 0.512259 -0.067836 + 0.561057 -0.061299 + 0.605070 -0.053312 + 0.645000 -0.044314 + 0.681569 -0.034760 + 0.715496 -0.025094 + 0.747503 -0.015741 + 0.778291 -0.007162 + 0.808052 0.000349 + 0.835995 0.006731 + 0.861180 0.011979 + 0.882675 0.016154 + 0.899562 0.019146 + 0.910935 0.020782 + 0.915849 0.020892 diff --git a/Matlab code/strut/CB40018.dat b/Matlab code/strut/CB40018.dat new file mode 100755 index 0000000..7e59a7c --- /dev/null +++ b/Matlab code/strut/CB40018.dat @@ -0,0 +1,60 @@ +Centerbody 4 + 0.913335 0.021890 + 0.877920 0.036739 + 0.821804 0.049876 + 0.751254 0.061793 + 0.672529 0.072440 + 0.591963 0.080485 + 0.515834 0.085551 + 0.448354 0.088233 + 0.389278 0.089240 + 0.337716 0.089099 + 0.292793 0.088100 + 0.253666 0.086521 + 0.219452 0.084540 + 0.189411 0.082295 + 0.162962 0.079792 + 0.139544 0.077056 + 0.118558 0.074088 + 0.099454 0.070872 + 0.081662 0.067405 + 0.065013 0.063573 + 0.049557 0.059256 + 0.035397 0.054309 + 0.022612 0.048573 + 0.011294 0.041892 + 0.001524 0.034156 + -0.006478 0.025521 + -0.012468 0.016180 + -0.016165 0.005614 + -0.017396 -0.003349 + -0.015880 -0.011133 + -0.013898 -0.019978 + -0.011515 -0.027052 + -0.006327 -0.035066 + 0.003113 -0.043699 + 0.018238 -0.052500 + 0.040470 -0.060992 + 0.071243 -0.068857 + 0.111748 -0.075911 + 0.160913 -0.081897 + 0.216504 -0.086498 + 0.276291 -0.089516 + 0.338024 -0.090767 + 0.399471 -0.090007 + 0.458394 -0.087074 + 0.512622 -0.081815 + 0.561398 -0.074424 + 0.605384 -0.065401 + 0.645284 -0.055237 + 0.681820 -0.044437 + 0.715714 -0.033494 + 0.747688 -0.022870 + 0.778445 -0.013063 + 0.808175 -0.004401 + 0.836091 0.003033 + 0.861250 0.009268 + 0.882720 0.014415 + 0.899584 0.018292 + 0.910941 0.020569 + 0.915849 0.020918 diff --git a/Matlab code/strut/CB600185b.dat b/Matlab code/strut/CB600185b.dat new file mode 100755 index 0000000..20fdd5b --- /dev/null +++ b/Matlab code/strut/CB600185b.dat @@ -0,0 +1,73 @@ + 1.00000 0.00000 + 0.97500 0.00996 + 0.95000 0.01900 + 0.92500 0.02718 + 0.90000 0.03460 + 0.87500 0.04131 + 0.85000 0.04739 + 0.82500 0.05288 + 0.80000 0.05785 + 0.77500 0.06232 + 0.75000 0.06636 + 0.72500 0.06998 + 0.70000 0.07325 + 0.67500 0.07617 + 0.65000 0.07879 + 0.62500 0.08112 + 0.60000 0.08320 + 0.55000 0.08664 + 0.50000 0.08924 + 0.45000 0.09109 + 0.40000 0.09218 + 0.35000 0.09250 + 0.30000 0.09204 + 0.25000 0.09067 + 0.20000 0.08803 + 0.17500 0.08599 + 0.15000 0.08328 + 0.12500 0.07968 + 0.10000 0.07485 + 0.07500 0.06855 + 0.05000 0.05962 + 0.03750 0.05414 + 0.02500 0.04820 + 0.01250 0.03472 + 0.00652 0.03090 + 0.00200 0.01606 + 0.00000 0.00000 + 0.00200 -0.01606 + 0.00652 -0.03090 + 0.01250 -0.03472 + 0.02500 -0.04820 + 0.03750 -0.05414 + 0.05000 -0.05962 + 0.07500 -0.06855 + 0.10000 -0.07485 + 0.12500 -0.07968 + 0.15000 -0.08328 + 0.17500 -0.08599 + 0.20000 -0.08803 + 0.25000 -0.09067 + 0.30000 -0.09204 + 0.35000 -0.09250 + 0.40000 -0.09218 + 0.45000 -0.09109 + 0.50000 -0.08924 + 0.55000 -0.08664 + 0.60000 -0.08320 + 0.62500 -0.08112 + 0.65000 -0.07879 + 0.67500 -0.07617 + 0.70000 -0.07325 + 0.72500 -0.06998 + 0.75000 -0.06636 + 0.77500 -0.06232 + 0.80000 -0.05785 + 0.82500 -0.05288 + 0.85000 -0.04739 + 0.87500 -0.04131 + 0.90000 -0.03460 + 0.92500 -0.02718 + 0.95000 -0.01900 + 0.97500 -0.00996 + 1.00000 0.00000 \ No newline at end of file diff --git a/Matlab code/strut/FFunc1.m b/Matlab code/strut/FFunc1.m new file mode 100755 index 0000000..eee0e77 --- /dev/null +++ b/Matlab code/strut/FFunc1.m @@ -0,0 +1,10 @@ + function FF = FFunc1(theta,P); + + % Derivative of function 1 + + FF=derppval(P,theta)*sin(theta)+ppval(P,theta)*cos(theta); + if theta < 0 + FF=-2*theta+pi; + elseif theta > pi + FF=-2*theta+pi; + end; \ No newline at end of file diff --git a/Matlab code/strut/Func1.m b/Matlab code/strut/Func1.m new file mode 100755 index 0000000..04060ee --- /dev/null +++ b/Matlab code/strut/Func1.m @@ -0,0 +1,10 @@ + function F = Func1(theta,P,yrqd); + + % Derivative of function 1 + + F=ppval(P,theta)*sin(theta)-yrqd; + if theta < 0 + F=-theta^2+pi*theta-yrqd; + elseif theta > pi + F=-theta^2+pi*theta-yrqd; + end; \ No newline at end of file diff --git a/Matlab code/strut/GB30015.dat b/Matlab code/strut/GB30015.dat new file mode 100755 index 0000000..f2f3ef6 --- /dev/null +++ b/Matlab code/strut/GB30015.dat @@ -0,0 +1,60 @@ +Centerbody 3 + 0.927434 0.030867 + 0.885738 0.037894 + 0.832426 0.044544 + 0.770708 0.050733 + 0.703824 0.054767 + 0.634967 0.057296 + 0.567289 0.058793 + 0.503215 0.059528 + 0.443412 0.059717 + 0.388348 0.059516 + 0.338469 0.059099 + 0.294235 0.058631 + 0.256072 0.058263 + 0.223760 0.058026 + 0.196178 0.057792 + 0.172167 0.057433 + 0.150558 0.056791 + 0.130182 0.055719 + 0.109959 0.054041 + 0.089801 0.051717 + 0.070408 0.048804 + 0.052499 0.045333 + 0.036815 0.041386 + 0.024065 0.037043 + 0.014845 0.032427 + 0.008795 0.027556 + 0.005152 0.022433 + 0.003127 0.017031 + 0.001941 0.011266 + 0.000833 0.004850 + 0.000868 -0.006228 + 0.002777 -0.014501 + 0.006960 -0.024027 + 0.014590 -0.033727 + 0.026905 -0.043466 + 0.045147 -0.053006 + 0.070516 -0.061993 + 0.104060 -0.070058 + 0.145165 -0.076927 + 0.192399 -0.082424 + 0.244294 -0.086545 + 0.299425 -0.089280 + 0.356322 -0.090523 + 0.413532 -0.090135 + 0.469635 -0.087990 + 0.523580 -0.084127 + 0.574750 -0.078781 + 0.622524 -0.072162 + 0.666283 -0.064484 + 0.705419 -0.055972 + 0.739322 -0.046855 + 0.767373 -0.037351 + 0.789853 -0.027657 + 0.808793 -0.017830 + 0.826372 -0.007917 + 0.844831 0.002026 + 0.866348 0.011975 + 0.893151 0.021929 + 0.927426 0.031964 diff --git a/Matlab code/strut/Newton.m b/Matlab code/strut/Newton.m new file mode 100755 index 0000000..ecc75fd --- /dev/null +++ b/Matlab code/strut/Newton.m @@ -0,0 +1,61 @@ +function x=newton(Fs,FPs,P0,y,P,TOL); + % NEWTON-RAPHSON ALGORITHM 2.3 + % + % To find a solution to f(x) = 0 given an + % initial approximation p0: + % + % y,P can be used for additional info if the function + % requires it. + % + % Initially written by Burden and Faires, revised by + % B.A. Broughton, 10/01/1999 + % + % INPUT: initial approximation p0; tolerance TOL; + % maximum number of iterations NO. + % + % OUTPUT: approximate solution p or a message of failure + + TRUE = 1; + FALSE = 0; + F = inline(Fs,'x','P','y'); + FP = inline(FPs,'x','P'); + NO=150; + OUP = 1; + F0 = F(P0,P,y); + % STEP 1 + I = 1; + OK = TRUE; +% STEP 2 + while I <= NO & OK == TRUE + % STEP 3 + % compute P(I) + FP0 = FP(P0,P); + D = F0/FP0; + % STEP 6 + P0 = P0 - D; + F0 = F(P0,P,y); + % STEP 4 + if abs(D) < TOL + % procedure completed successfully + % fprintf(OUP,'\nApproximate solution = %.10e\n',P0); + % fprintf(OUP,'with F(P) = %.10e\n',F0); + % fprintf(OUP,'Number of iterations = %d\n',I); + % fprintf(OUP,'Tolerance = %.10e\n',TOL); + OK = FALSE; + % STEP 5 + else + I = I+1; + end + end + if OK == TRUE +% STEP 7 +% procedure completed unsuccessfully + fprintf(OUP,'\nIteration number %d',NO); + fprintf(OUP,' gave approximation %.10e\n',P0); + fprintf(OUP,'with F(P) = %.10e not within tolerance %.10e\n',F0,TOL); + end + x = P0; + + + + \ No newline at end of file diff --git a/Matlab code/strut/default.dat b/Matlab code/strut/default.dat new file mode 100755 index 0000000..79d7d38 --- /dev/null +++ b/Matlab code/strut/default.dat @@ -0,0 +1,4 @@ +Strut length: +4.0 +Strut width: +1.5 \ No newline at end of file diff --git a/Matlab code/strut/derppval.m b/Matlab code/strut/derppval.m new file mode 100755 index 0000000..6be35ab --- /dev/null +++ b/Matlab code/strut/derppval.m @@ -0,0 +1,48 @@ +function v=derppval(pp,xx) +%PPVAL Evaluate piecewise polynomial. +% V = PPVAL(PP,XX) returns the value at the points XX of the +% piecewise polynomial contained in PP, as constructed by SPLINE +% (or MKPP). +% +% Revised by B.A. Broughton on 10/01/1999 to calculate the derivative +% for a pre-fitted cubic spline in the points xx +% +% See also SPLINE. + +% Carl de Boor 7-2-86 +% Revised 10-14-97 CB to speed up locating points in mesh (as in +% PPUAL) and to handle vector-valued functions. +% Copyright (c) 1984-98 by The MathWorks, Inc. +% $Revision: 5.8 $ $Date: 1997/11/21 23:41:00 $ + +[mx,nx] = size(xx); lx = mx*nx; xs = reshape(xx,1,lx); +% if necessary, sort xx +tosort=0; +if any(diff(xs)<0) + tosort=1;[xs,ix]=sort(xs); +end + +% take apart pp +[x,c,l,k,d]=unmkpp(pp); + +% for each data point, compute its breakpoint interval +[ignored,index] = sort([x(1:l) xs]); +index = max([find(index>l)-(1:lx);ones(1,lx)]); + +% now go to local coordinates ... +xs = xs-x(index); + +if d>1 % ... replicate xs and index in case pp is vector-valued ... + xs = reshape(xs(ones(d,1),:),1,d*lx); + index = d*index; temp = [-d:-1].'; + index = reshape(1+index(ones(d,1),:)+temp(:,ones(1,lx)), d*lx, 1 ); +end + +% ... and apply nested multiplication to get derivative: + v = 3*c(index,1).'; + for i=2:k-1 + v = xs.*v + (4-i)*c(index,i).'; + end +v = reshape(v,d,lx); +if tosort>0, v(:,ix) = v; end +v = reshape(v,d*mx,nx); diff --git a/Matlab code/strut/e169.dat b/Matlab code/strut/e169.dat new file mode 100755 index 0000000..d6ae0ac --- /dev/null +++ b/Matlab code/strut/e169.dat @@ -0,0 +1,61 @@ + 1.00000 0.00000 + 0.99640 0.00022 + 0.98598 0.00115 + 0.96948 0.00290 + 0.94737 0.00514 + 0.91970 0.00771 + 0.88673 0.01081 + 0.84899 0.01458 + 0.80708 0.01904 + 0.76168 0.02416 + 0.71346 0.02985 + 0.66316 0.03596 + 0.61148 0.04231 + 0.55912 0.04866 + 0.50675 0.05477 + 0.45499 0.06036 + 0.40442 0.06516 + 0.35555 0.06889 + 0.30884 0.07127 + 0.26456 0.07202 + 0.22289 0.07110 + 0.18408 0.06858 + 0.14839 0.06450 + 0.11605 0.05896 + 0.08721 0.05212 + 0.06206 0.04427 + 0.04085 0.03567 + 0.02379 0.02657 + 0.01106 0.01729 + 0.00290 0.00819 + 0.00000 0.00000 + 0.00290 -0.00819 + 0.01106 -0.01729 + 0.02379 -0.02657 + 0.04085 -0.03567 + 0.06206 -0.04427 + 0.08721 -0.05212 + 0.11605 -0.05896 + 0.14839 -0.06450 + 0.18408 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fitting program +------------------------------- + +Make sure that all the .m files are in the same directory. Your +airfoil coordinate files do not have to be in the same directory. + +Make sure that the first line in the airfoil coordinate file is not +the name of the airfoil, i.e. only numbers are allowed in the file. +Also make sure the coordinates are sorted TE-LE-TE and that the +leading edge point (usually 0,0) is not repeated. This is important, +since it is easy to forget to remove the extra point if you sorted the +coordinates with a spreadsheet such as MS Excel. + +Start Matlab. +Change the directory to the directory with the .m files. Use the "cd" +command in Matlab to do this. +Run the GUI by typing "strut". + +Now you can load an airfoil by clicking on the "load" button. Simply +choose the file. After loading the filename of the current airfoil, +the name of the filename will appear in the box below the "load" +button. + +The size of the strut can be changed by changing the values for +"length" and "width". "Length" is the distance in the chordwise +direction. Units do not matter. You can also change the default +values by editing the "default.dat" text file. + +Click on "calculate", wait a couple of seconds and the information for +the fitted airfoil should appear in the three remaining boxes. The +values are: + +scale - How much you must enlarge the airfoil to fit over the box. +xLE% - Chord percentage where the leading edge of the strut is located. +xLE - Actual distance from the LE of the airfoil to the LE of the + strut. + +Notes: +------ + +The program will not converge for low aspect ratio struts in very thin +airfoils. It should however work for all practical cases for the AE +416 homework assignment. + + + +********************************************************************** +Development Notes +********************************************************************** + +1) Matlab program for sizing airfoils to fit over a rectangular + strut written Sept 1999 by + + B.A. Broughton + Graduate Student + Applied Aerodynamics Group + Dept. of Aerospace Engineering + University of Illinois at Urbana-Champaign + + +2) Minor fixes/updates/changes by Selig 090925 + + +~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ diff --git a/Matlab code/strut/reversefit.m b/Matlab code/strut/reversefit.m new file mode 100755 index 0000000..f34144b --- /dev/null +++ b/Matlab code/strut/reversefit.m @@ -0,0 +1,7 @@ +function theta=reversefit(P,y,theta0); + +TOL=1e-8; +F='Func1(x,P,y)'; +FP='FFunc1(x,P)'; +theta=Newton(F,FP,theta0,y,P,TOL); + diff --git a/Matlab code/strut/strut.m b/Matlab code/strut/strut.m new file mode 100755 index 0000000..c00bb9c --- /dev/null +++ b/Matlab code/strut/strut.m @@ -0,0 +1,194 @@ +function fig = strut() +% This is the machine-generated representation of a Handle Graphics object +% and its children. Note that handle values may change when these objects +% are re-created. This may cause problems with any callbacks written to +% depend on the value of the handle at the time the object was saved. +% This problem is solved by saving the output as a FIG-file. +% +% To reopen this object, just type the name of the M-file at the MATLAB +% prompt. The M-file and its associated MAT-file must be on your path. +% +% NOTE: certain newer features in MATLAB may not have been saved in this +% M-file due to limitations of this format, which has been superseded by +% FIG-files. Figures which have been annotated using the plot editor tools +% are incompatible with the M-file/MAT-file format, and should be saved as +% FIG-files. + +load strut + +h0 = figure('Color',[0.8 0.8 0.8], ... + 'Colormap',mat0, ... + 'FileName','strut.m', ... + 'PaperPosition',[18 180 576 432], ... + 'PaperUnits','points', ... + 'Position',[392 219 560 420], ... + 'Tag','Fig1', ... + 'ToolBar','none'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'Callback','strutcall load', ... + 'ListboxTop',0, ... + 'Position',[356.25 289.5 50.25 15.75], ... + 'String','Load Airfoil', ... + 'Tag','Pushbutton1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 248.25 40 11], ... + 'String','Strut Size:', ... + 'Style','text', ... + 'Tag','StaticText1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 228.75 30 11.25], ... + 'String','Width', ... + 'Style','text', ... + 'Tag','StaticText1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 208.625 30 11], ... + 'String','Length', ... + 'Style','text', ... + 'Tag','StaticText1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'ListboxTop',0, ... + 'Position',[377.25 226.5 39.75 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','width'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'ListboxTop',0, ... + 'Position',[377.25 206.25 39.75 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','length'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'Callback','strutcall calculate', ... + 'ListboxTop',0, ... + 'Position',[356.25 177 50.25 15.75], ... + 'String','Calculate', ... + 'Tag','Pushbutton1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'ListboxTop',0, ... + 'Position',[347.25 133.5 30 11.25], ... + 'String','Scale', ... + 'Style','text', ... + 'Tag','StaticText2'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[347.25 88.875 30 11.25], ... + 'String','Xle (%)', ... + 'Style','text', ... + 'Tag','StaticText2'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[347.25 44.25 30 11.25], ... + 'String','Xle', ... + 'Style','text', ... + 'Tag','StaticText2'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[354.75 114 50.25 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','scale'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[354.75 69.375 50.25 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','xlepers'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[354.75 24.75 50.25 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','xle'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 152.25 40 12], ... + 'String','Results:', ... + 'Style','text', ... + 'Tag','StaticText3'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[347.25 264.75 66 15.75], ... + 'String','None Selected', ... + 'Style','edit', ... + 'Tag','airfoilname'); +h1 = axes('Parent',h0, ... + 'Units','pixels', ... + 'CameraUpVector',[0 1 0], ... + 'CameraUpVectorMode','manual', ... + 'Color',[1 1 1], ... + 'ColorOrder',mat1, ... + 'Position',[34 27 418 386], ... + 'Tag','Axes1', ... + 'XColor',[0 0 0], ... + 'YColor',[0 0 0], ... + 'ZColor',[0 0 0]); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','center', ... + 'Position',[0.4988009592326139 -0.06233766233766236 9.160254037844386], ... + 'Tag','Axes1Text4', ... + 'VerticalAlignment','cap'); +set(get(h2,'Parent'),'XLabel',h2); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','center', ... + 'Position',[-0.06954436450839328 0.4961038961038962 9.160254037844386], ... + 'Rotation',90, ... + 'Tag','Axes1Text3', ... + 'VerticalAlignment','baseline'); +set(get(h2,'Parent'),'YLabel',h2); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','right', ... + 'Position',[-0.0815347721822542 1.018181818181818 9.160254037844386], ... + 'Tag','Axes1Text2', ... + 'Visible','off'); +set(get(h2,'Parent'),'ZLabel',h2); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','center', ... + 'Position',[0.4988009592326139 1.018181818181818 9.160254037844386], ... + 'Tag','Axes1Text1', ... + 'VerticalAlignment','bottom'); +set(get(h2,'Parent'),'Title',h2); +if nargout > 0, fig = h0; end diff --git a/Matlab code/strut/strut.mat b/Matlab code/strut/strut.mat new file mode 100755 index 0000000..e502961 Binary files /dev/null and b/Matlab code/strut/strut.mat differ diff --git a/Matlab code/strut/strutWindow.png b/Matlab code/strut/strutWindow.png new file mode 100755 index 0000000..acd85bf Binary files /dev/null and b/Matlab code/strut/strutWindow.png differ diff --git a/Matlab code/strut/strutcall.m b/Matlab code/strut/strutcall.m new file mode 100755 index 0000000..6497900 --- /dev/null +++ b/Matlab code/strut/strutcall.m @@ -0,0 +1,110 @@ +function strutcall(action) + +global x y tmax +% Remove +global P + +switch(action) +case 'load' + + % Read Input Data + [fname,pname] = uigetfile('*.*','File containing airfoil co-ordinates'); + if fname == 0 + return; + end + + dot=find(fname=='.'); + + oldpath = pwd; + eval(['cd ' pname]); + data = load(fname); + eval(['cd ' oldpath]); + + x = data(:,1); + y = data(:,2); + + txtHndl=findobj(gcbf,'Tag','airfoilname'); + set(txtHndl,'String',fname(1:dot-1)); + + plot(x,y); axis([0 1 -.5 .5]); + + % Load default strut size + fid=fopen('default.dat','r'); + fgetl(fid); + lstrut=eval(fgetl(fid)); + fgetl(fid); + wstrut=eval(fgetl(fid)); + fclose(fid); + + txtHndl=findobj(gcbf,'Tag','length'); + set(txtHndl,'String',num2str(lstrut)); + + txtHndl=findobj(gcbf,'Tag','width'); + set(txtHndl,'String',num2str(wstrut)); + +case 'calculate' + + global x y + delt=1e-7; % Used for calculating dF/dt + TOL=1e-6; % Tolerance for N-R iteration + + N = length(x); + c = max(x)-min(x); + x1 = x-c/2; + r = sqrt(x1.^2+y.^2); + theta = acos(x1./r); + % Use a continues theta + theta((N+1)/2:N)=2*pi-theta((N+1)/2:N); + P = spline(theta,r); % Fit cubic spline in polar coords + + txtHndl=findobj(gcbf,'Tag','length'); + lstrut=eval(get(txtHndl,'String')); + + txtHndl=findobj(gcbf,'Tag','width'); + tstrut=eval(get(txtHndl,'String')); + + ARrqd=lstrut/tstrut; % AR of strut + + [tmax,I]=max(y); % Approx. max thickness + tmax=tmax*2; + + t0=tmax/2; % Start with tmax/2 + + F='ARfit(P,x)-y'; % For sol. F=AR(t)-ARrqd=0 + FP=['(ARfit(P,x+' num2str(delt) ')-(ARfit(P,x)))/' num2str(delt)]; + % Derivative: F'=(F(t+dt)-F(t))/dt + + tnew=Newton(F,FP,t0,ARrqd,P,TOL); + % Find size of strut that will fit in norm. airfoil + + [AR,xLEnew]=ARfit(P,tnew); + + % Scale + scale = tstrut/tnew; + chord=scale*c; + xLEnewnorm = xLEnew+c/2; + xLEnew = xLEnewnorm*scale; + + x1=x*scale; + y1=y*scale; + + % Plotit + c1x=xLEnew; cy=tstrut/2; + c2x=xLEnew+lstrut; + strx=[c1x c2x c2x c1x c1x]; + stry=[cy cy -cy -cy cy]; + plot(x1,y1,'b',strx,stry,'r'); + axis([0 chord -chord/2 chord/2]); + + txtHndl=findobj(gcbf,'Tag','scale'); + set(txtHndl,'String',num2str(scale)); + + txtHndl=findobj(gcbf,'Tag','xlepers'); + set(txtHndl,'String',num2str(xLEnewnorm*100)); + + txtHndl=findobj(gcbf,'Tag','xle'); + set(txtHndl,'String',num2str(xLEnew)); + + + +end; diff --git a/Matlab code/strut/strutcall_update.m b/Matlab code/strut/strutcall_update.m new file mode 100755 index 0000000..bd414c8 --- /dev/null +++ b/Matlab code/strut/strutcall_update.m @@ -0,0 +1,110 @@ +function strutcall(action) + +global x y tmax +% Remove +global P + +switch(action) +case 'load' + + % Read Input Data + [fname,pname] = uigetfile('*.dat','File containing airfoil co-ordinates'); + if fname == 0 + return; + end + + dot=find(fname=='.'); + + oldpath = pwd; + eval(['cd ' pname]); + data = load(fname); + eval(['cd ' pwd]); + + x = data(:,1); + y = data(:,2); + + txtHndl=findobj(gcbf,'Tag','airfoilname'); + set(txtHndl,'String',fname(1:dot-1)); + + plot(x,y); axis([0 1 -.5 .5]); + + % Load default strut size + fid=fopen('default.dat','r'); + fgetl(fid); + lstrut=eval(fgetl(fid)); + fgetl(fid); + wstrut=eval(fgetl(fid)); + fclose(fid); + + txtHndl=findobj(gcbf,'Tag','length'); + set(txtHndl,'String',num2str(lstrut)); + + txtHndl=findobj(gcbf,'Tag','width'); + set(txtHndl,'String',num2str(wstrut)); + +case 'calculate' + + global x y + delt=1e-7; % Used for calculating dF/dt + TOL=1e-6; % Tolerance for N-R iteration + + N = length(x); + c = max(x)-min(x); + x1 = x-c/2; + r = sqrt(x1.^2+y.^2); + theta = acos(x1./r); + % Use a continues theta + theta((N+1)/2:N)=2*pi-theta((N+1)/2:N); + P = spline(theta,r); % Fit cubic spline in polar coords + + txtHndl=findobj(gcbf,'Tag','length'); + lstrut=eval(get(txtHndl,'String')); + + txtHndl=findobj(gcbf,'Tag','width'); + tstrut=eval(get(txtHndl,'String')); + + ARrqd=lstrut/tstrut; % AR of strut + + [tmax,I]=max(y); % Approx. max thickness + tmax=tmax*2; + + t0=tmax/2; % Start with tmax/2 + + F='ARfit(P,x)-y'; % For sol. F=AR(t)-ARrqd=0 + FP=['(ARfit(P,x+' num2str(delt) ')-(ARfit(P,x)))/' num2str(delt)]; + % Derivative: F'=(F(t+dt)-F(t))/dt + + tnew=Newton(F,FP,t0,ARrqd,P,TOL); + % Find size of strut that will fit in norm. airfoil + + [AR,xLEnew]=ARfit(P,tnew); + + % Scale + scale = tstrut/tnew; + chord=scale*c; + xLEnewnorm = xLEnew+c/2; + xLEnew = xLEnewnorm*scale; + + x1=x*scale; + y1=y*scale; + + % Plotit + c1x=xLEnew; cy=tstrut/2; + c2x=xLEnew+lstrut; + strx=[c1x c2x c2x c1x c1x]; + stry=[cy cy -cy -cy cy]; + plot(x1,y1,'b',strx,stry,'r'); + axis([0 chord -chord/2 chord/2]); + + txtHndl=findobj(gcbf,'Tag','scale'); + set(txtHndl,'String',num2str(scale)); + + txtHndl=findobj(gcbf,'Tag','xlepers'); + set(txtHndl,'String',num2str(xLEnewnorm*100)); + + txtHndl=findobj(gcbf,'Tag','xle'); + set(txtHndl,'String',num2str(xLEnew)); + + + +end; \ No newline at end of file diff --git a/Matlab code/strut/strutfit.m b/Matlab code/strut/strutfit.m new file mode 100755 index 0000000..06e0ff3 --- /dev/null +++ b/Matlab code/strut/strutfit.m @@ -0,0 +1,208 @@ +function fig = strut() +% This is the machine-generated representation of a Handle Graphics object +% and its children. Note that handle values may change when these objects +% are re-created. This may cause problems with any callbacks written to +% depend on the value of the handle at the time the object was saved. +% This problem is solved by saving the output as a FIG-file. +% +% To reopen this object, just type the name of the M-file at the MATLAB +% prompt. The M-file and its associated MAT-file must be on your path. +% +% NOTE: certain newer features in MATLAB may not have been saved in this +% M-file due to limitations of this format, which has been superseded by +% FIG-files. Figures which have been annotated using the plot editor tools +% are incompatible with the M-file/MAT-file format, and should be saved as +% FIG-files. + +load strut + +h0 = figure('Color',[0.8 0.8 0.8], ... + 'Colormap',mat0, ... + 'FileName','strutfit.m', ... + 'MenuBar','none', ... + 'PaperPosition',[18 180 576 432], ... + 'PaperUnits','points', ... + 'Position',[392 219 560 420], ... + 'Tag','Fig1', ... + 'ToolBar','none', ... + 'NumberTitle','off', ... + 'Name','Strutfit'); +h1 = uimenu('Parent',h0, ... + 'Label','Help', ... + 'Tag','uimenu1'); +h2 = uimenu('Parent',h1, ... + 'Callback','edit readme.txt', ... + 'Label','Readme', ... + 'Tag','Helpuimenu1'); +h2 = uimenu('Parent',h1, ... + 'Callback','edit about.txt', ... + 'Label','About Strutfit', ... + 'Tag','Aboutuimenu1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'Callback','strutcall load', ... + 'ListboxTop',0, ... + 'Position',[356.25 289.5 50.25 15.75], ... + 'String','Load Airfoil', ... + 'Tag','Pushbutton1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 248.25 40 11], ... + 'String','Strut Size:', ... + 'Style','text', ... + 'Tag','StaticText1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 228.75 30 11.25], ... + 'String','Width', ... + 'Style','text', ... + 'Tag','StaticText1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 208.625 30 11], ... + 'String','Length', ... + 'Style','text', ... + 'Tag','StaticText1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'ListboxTop',0, ... + 'Position',[377.25 226.5 39.75 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','width'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'ListboxTop',0, ... + 'Position',[377.25 206.25 39.75 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','length'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'Callback','strutcall calculate', ... + 'ListboxTop',0, ... + 'Position',[356.25 177 50.25 15.75], ... + 'String','Calculate', ... + 'Tag','Pushbutton1'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'ListboxTop',0, ... + 'Position',[347.25 133.5 30 11.25], ... + 'String','Scale', ... + 'Style','text', ... + 'Tag','StaticText2'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[347.25 88.875 30 11.25], ... + 'String','Xle (%)', ... + 'Style','text', ... + 'Tag','StaticText2'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[347.25 44.25 30 11.25], ... + 'String','Xle', ... + 'Style','text', ... + 'Tag','StaticText2'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[354.75 114 50.25 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','scale'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[354.75 69.375 50.25 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','xlepers'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[354.75 24.75 50.25 15.75], ... + 'String','0', ... + 'Style','edit', ... + 'Tag','xle'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[0.752941176470588 0.752941176470588 0.752941176470588], ... + 'ListboxTop',0, ... + 'Position',[341.25 152.25 40 12], ... + 'String','Results:', ... + 'Style','text', ... + 'Tag','StaticText3'); +h1 = uicontrol('Parent',h0, ... + 'Units','points', ... + 'BackgroundColor',[1 1 1], ... + 'Enable','off', ... + 'ListboxTop',0, ... + 'Position',[347.25 264.75 66 15.75], ... + 'String','None Selected', ... + 'Style','edit', ... + 'Tag','airfoilname'); +h1 = axes('Parent',h0, ... + 'Units','pixels', ... + 'CameraUpVector',[0 1 0], ... + 'CameraUpVectorMode','manual', ... + 'Color',[1 1 1], ... + 'ColorOrder',mat1, ... + 'Position',[34 27 418 386], ... + 'Tag','Axes1', ... + 'XColor',[0 0 0], ... + 'YColor',[0 0 0], ... + 'ZColor',[0 0 0]); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','center', ... + 'Position',[0.4988009592326139 -0.06233766233766236 9.160254037844386], ... + 'Tag','Axes1Text4', ... + 'VerticalAlignment','cap'); +set(get(h2,'Parent'),'XLabel',h2); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','center', ... + 'Position',[-0.06954436450839328 0.4961038961038962 9.160254037844386], ... + 'Rotation',90, ... + 'Tag','Axes1Text3', ... + 'VerticalAlignment','baseline'); +set(get(h2,'Parent'),'YLabel',h2); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','right', ... + 'Position',[-0.0815347721822542 1.018181818181818 9.160254037844386], ... + 'Tag','Axes1Text2', ... + 'Visible','off'); +set(get(h2,'Parent'),'ZLabel',h2); +h2 = text('Parent',h1, ... + 'Color',[0 0 0], ... + 'HandleVisibility','off', ... + 'HorizontalAlignment','center', ... + 'Position',[0.4988009592326139 1.018181818181818 9.160254037844386], ... + 'Tag','Axes1Text1', ... + 'VerticalAlignment','bottom'); +set(get(h2,'Parent'),'Title',h2); +if nargout > 0, fig = h0; end diff --git a/Matlab code/superGrimace.m b/Matlab code/superGrimace.m new file mode 100755 index 0000000..8e0fcdf --- /dev/null +++ b/Matlab code/superGrimace.m @@ -0,0 +1,451 @@ +%superGrimace +%all alfas in DEGREES! +%by ascorrea, with help from Jacob Huffman and Omkar Shetty +%"filler" variable just makes it easier to switch between Ronald and Grimace + +function superGrimace(paramfile, pranformfile, pranformConstraint) +testrange={'20'}; + +for testnumber=1:length(testrange) +prefix='FDR0'; +name=strcat(prefix, testrange{testnumber}); +paramfile=strcat(name, '.param'); +pranformfile=strcat(name, '.plan', ''); +fprintf('%s \n', name) + + +%LOCATIONS--------------------------------------------------------------] +rootLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Matlab Code'; +airfoilLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Airfoils'; +pranformLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planforms'; +pranformConstraintLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planform Constraints'; +paramLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Parameter Files'; +outputsLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/superGrimace Outputs'; +%-----------------------------------------------------------------------] +spanwiseresolution=50; +chordwiseresolution=100; + +cd(paramLOCATION); +[variablenames, variablevalues]=textread(paramfile, '%s %f'); +cd(pranformLOCATION) +[spans, chords, offsets, airfoil]=textread(pranformfile, '%f %f %f %s'); +cd(pranformConstraintLOCATION) +[spansCONST, chordsCONST, offsetsCONST, heightCONST]=textread(pranformConstraint, '%f %f %f %f'); +cd(rootLOCATION) + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end + +cd(airfoilLOCATION) + +[surfplotY surfplotX thicknessplot]=findthicknessplot(airfoil, chords, spans, offsets, spanwiseresolution, chordwiseresolution); +[wakeplot]=findwakeplot(chords, spans, alt_cruise, M_cruise, laminarflow_cruise, fuse_width, spanwiseresolution, chordwiseresolution); +plotitle=regexprep(pranformfile, '.plan', ''); + +cd(outputsLOCATION) +% clf +% hold on +% surf(surfplotY, -surfplotX, thicknessplot, 'LineStyle', 'none') +% surf(-surfplotY,-surfplotX, thicknessplot, 'LineStyle', 'none') +% title(plotitle) +% axis off +% axis equal +% colorbar +% view(2) +% filename=regexprep(pranformfile, '.plan', '_surfacev1.tiff'); +% print (gcf, '-dtiff', filename) +% clf +% hold on +% surf(surfplotY, surfplotX, thicknessplot, 'LineStyle', 'none') +% surf(-surfplotY, surfplotX, thicknessplot, 'LineStyle', 'none') +% axis equal +% axis off +% colorbar +% view(3) +% title(plotitle) +% filename=regexprep(pranformfile, '.plan', '_surfacev2.tiff'); +% print (gcf, '-dtiff', filename) + +clf +hold on +surf(surfplotY, -surfplotX, wakeplot, 'LineStyle', 'none') +surf(-surfplotY,-surfplotX, wakeplot, 'LineStyle', 'none') +title(plotitle) +axis off +axis equal +colorbar +view(2) +filename=regexprep(pranformfile, '.plan', '_BLthicknessv1.tiff'); +print (gcf, '-dtiff', filename) + +clf +hold on +surf(-surfplotY, -surfplotX, wakeplot, 'LineStyle', 'none') +surf(-surfplotY, -surfplotX, wakeplot, 'LineStyle', 'none') +axis off +axis([-80 80 -160 0 0 1]) +colorbar +view(3) +title(plotitle) +filename=regexprep(pranformfile, '.plan', '_BLthicknessv2.tiff'); +print (gcf, '-dtiff', filename) + + +axis equal +axis off +hold off + +cd(rootLOCATION) +end +clc +fprintf('You are welcome\n') +end + +function [plotLE plotTE]=plotpranform(spans, chords, offsets, n) +Chords = findChords(n, chords, spans); + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [plotLE plotTE]=plotconstraint(spans, chords, offsets, n) + +%plot constraint +for i = 1:(size(chords)-1) + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + yplotLE(i,j) = offsets(i+1); + end +end + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) (-yplotLE(i,j)-chords(i+1))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function plotThick=plotThick(spans, chords, offsets, airfoil, h, n) +n=n/10; +Chords = findChords(n, chords, spans); +plotThickLE=zeros(1,2); +plotThickTE=zeros(1,2); + +for i = 1:(size(chords)-1) + for j = 1:n + + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + chordloc=linspace(0, Chords(i,j)); + + for k=1:length(chordloc)-1 + thicknessLE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(k)); + clc + fprintf('%g:%u:%u:%u/%g:%u:%u:%u',h,i,j,k,h,(length(chords)-1),n,(length(chordloc)-1)) + if thicknessLE(k)>=h + plotThickLE=[plotThickLE; xplotLE(i,j) -(chordloc(k)+yplotLE(i,j))]; + break + end + end + + for k=1:length(chordloc)-1 + thicknessTE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(length(chordloc)-k)); + if thicknessTE(k)>=h + plotThickTE=[plotThickTE; xplotLE(i,j) -(chordloc(length(chordloc)-k)+yplotLE(i,j))]; + break + end + end + + end + +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +plotThickLE(1,:)=[]; +plotThickTE(1,:)=[]; +plotThick=[plotThickLE; flipud(plotThickTE)]; +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLocwidth + lam=laminarflow; + else + lam=laminarflow-.15; + end + x=linspace(0, Chords(i,j),reso); + for k = 1:length(x) + if (k <= 100*lam) + delta_x=( 5.2 * x(k) )*(v_fps*x(k)/dynvisc)^-0.5; + wake(k,j)= delta_x; + else %if turbulent + x_tr=x(100*lam); + Re_xtr = v_fps * x_tr / dynvisc; + delta_xtr=(5.2*x_tr)*(v_fps*x(k)/dynvisc)^-(0.5); + delta_l = ((delta_xtr*((v_fps)^0.2))/(0.37*((dynvisc)^0.2)))^(1/0.8); + lt = x(k) - x_tr + delta_l; + Re_lt = v_fps * lt / dynvisc; + delta = 0.37 * lt /(Re_lt)^0.2; + wake(k,j) = delta; + end + end +wakeplot=[wakeplot, wake]; + end + +fprintf('Wake plot: %6.2f percent complete\n', 100*(i+.1*j)/((length(chords)-1)+ n*.1)) +end +wakeplot(1,:)=[]; +wakeplot(:,1)=[ ]; +flipud(wakeplot); +end +function q=finddynpress(alt, v_mach) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +%slpcuft: clugs ber cubic foot +density_slpcuft=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density_slpcuft*v_fps^2; +end diff --git a/Matlab code/superGrimace.m~ b/Matlab code/superGrimace.m~ new file mode 100755 index 0000000..2beda72 --- /dev/null +++ b/Matlab code/superGrimace.m~ @@ -0,0 +1,450 @@ +%superGrimace +%all alfas in DEGREES! +%by ascorrea, with help from Jacob Huffman and Omkar Shetty +%"filler" variable just makes it easier to switch between Ronald and Grimace + +function superGrimace(paramfile, pranformfile, pranformConstraint) +testrange={'20'}; + +for testnumber=1:length(testrange) +prefix='FDR0'; +name=strcat(prefix, testrange{testnumber}); +paramfile=strcat(name, '.param'); +pranformfile=strcat(name, '.plan', ''); +fprintf('%s \n', name) + + +%LOCATIONS--------------------------------------------------------------] +rootLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Matlab Code'; +airfoilLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Airfoils'; +pranformLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planforms'; +pranformConstraintLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planform Constraints'; +paramLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Parameter Files'; +outputsLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/superGrimace Outputs'; +%-----------------------------------------------------------------------] +spanwiseresolution=50; +chordwiseresolution=100; + +cd(paramLOCATION); +[variablenames, variablevalues]=textread(paramfile, '%s %f'); +cd(pranformLOCATION) +[spans, chords, offsets, airfoil]=textread(pranformfile, '%f %f %f %s'); +cd(pranformConstraintLOCATION) +[spansCONST, chordsCONST, offsetsCONST, heightCONST]=textread(pranformConstraint, '%f %f %f %f'); +cd(rootLOCATION) + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end + +cd(airfoilLOCATION) + +[surfplotY surfplotX thicknessplot]=findthicknessplot(airfoil, chords, spans, offsets, spanwiseresolution, chordwiseresolution); +[wakeplot]=findwakeplot(chords, spans, alt_cruise, M_cruise, laminarflow_cruise, fuse_width, spanwiseresolution, chordwiseresolution); +plotitle=regexprep(pranformfile, '.plan', ''); + +cd(outputsLOCATION) +% clf +% hold on +% surf(surfplotY, -surfplotX, thicknessplot, 'LineStyle', 'none') +% surf(-surfplotY,-surfplotX, thicknessplot, 'LineStyle', 'none') +% title(plotitle) +% axis off +% axis equal +% colorbar +% view(2) +% filename=regexprep(pranformfile, '.plan', '_surfacev1.tiff'); +% print (gcf, '-dtiff', filename) +% clf +% hold on +% surf(surfplotY, surfplotX, thicknessplot, 'LineStyle', 'none') +% surf(-surfplotY, surfplotX, thicknessplot, 'LineStyle', 'none') +% axis equal +% axis off +% colorbar +% view(3) +% title(plotitle) +% filename=regexprep(pranformfile, '.plan', '_surfacev2.tiff'); +% print (gcf, '-dtiff', filename) + +clf +hold on +surf(surfplotY, -surfplotX, wakeplot, 'LineStyle', 'none') +surf(-surfplotY,-surfplotX, wakeplot, 'LineStyle', 'none') +title(plotitle) +axis off +axis equal +colorbar +view(2) +filename=regexprep(pranformfile, '.plan', '_BLthicknessv1.tiff'); +print (gcf, '-dtiff', filename) +clf +hold on +surf(-surfplotY, -surfplotX, wakeplot, 'LineStyle', 'none') +surf(-surfplotY, -surfplotX, wakeplot, 'LineStyle', 'none') +axis off +colorbar +view(3) +title(plotitle) +filename=regexprep(pranformfile, '.plan', '_BLthicknessv2.tiff'); +print (gcf, '-dtiff', filename) + + +axis equal +axis off +hold off + +cd(rootLOCATION) +end +clc +fprintf('You are welcome\n') +end + +function [plotLE plotTE]=plotpranform(spans, chords, offsets, n) +Chords = findChords(n, chords, spans); + +%plot planform +for i = 1:(size(chords)-1) + dist=0; + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + + + end +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function [plotLE plotTE]=plotconstraint(spans, chords, offsets, n) + +%plot constraint +for i = 1:(size(chords)-1) + for j = 1:n + dist = (spans(i+1)-spans(i))./n; + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + yplotLE(i,j) = offsets(i+1); + end +end + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) (-yplotLE(i,j)-chords(i+1))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +end +function plotThick=plotThick(spans, chords, offsets, airfoil, h, n) +n=n/10; +Chords = findChords(n, chords, spans); +plotThickLE=zeros(1,2); +plotThickTE=zeros(1,2); + +for i = 1:(size(chords)-1) + for j = 1:n + + Chords(i,j); + dist = (spans(i+1)-spans(i))./n; + + if i==1 + xplotLE(i,j+1)=spans(1)+dist*(j); + else + xplotLE(i,1)=xplotLE(i-1,end); + xplotLE(i,j+1)=xplotLE(i-1,end)+dist*(j); + end + + fitX(1)=spans(i); + fitX(2)=spans(i+1); + fitY(1)=offsets(i); + fitY(2)=offsets(i+1); + a = polyfit(fitX, fitY,1); + yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2); + + chordloc=linspace(0, Chords(i,j)); + + for k=1:length(chordloc)-1 + thicknessLE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(k)); + clc + fprintf('%g:%u:%u:%u/%g:%u:%u:%u',h,i,j,k,h,(length(chords)-1),n,(length(chordloc)-1)) + if thicknessLE(k)>=h + plotThickLE=[plotThickLE; xplotLE(i,j) -(chordloc(k)+yplotLE(i,j))]; + break + end + end + + for k=1:length(chordloc)-1 + thicknessTE(k)=findthickness(airfoil{i}, Chords(i,j), chordloc(length(chordloc)-k)); + if thicknessTE(k)>=h + plotThickTE=[plotThickTE; xplotLE(i,j) -(chordloc(length(chordloc)-k)+yplotLE(i,j))]; + break + end + end + + end + +end + + +plotLE=zeros(1,2); +plotTE=zeros(1,2); + +for i=1:(size(chords)-1) + for j=1:n + plotLE=[plotLE; xplotLE(i,j) -yplotLE(i,j)]; + plotTE=[plotTE; xplotLE(i,j) -(yplotLE(i,j)+Chords(i,j))]; + end +end + +plotTE(1,:)=[]; +plotLE(1,:)=[]; +plotThickLE(1,:)=[]; +plotThickTE(1,:)=[]; +plotThick=[plotThickLE; flipud(plotThickTE)]; +end +function thickness=findthickness(airfoil, Chord, xLoc) +Airfoil = load(airfoil); +Airfoil = Airfoil*Chord; +% blah....goodnight + + AirfoilX=Airfoil(:,1); + [min_diff, k]=min(abs(AirfoilX)); + + for j=1:k + AirfoilYupper(j)=Airfoil(j,2); + AirfoilXupper(j)=Airfoil(j,1); + end + + for j=1:length(Airfoil)-k + AirfoilYlower(j)=Airfoil(length(Airfoil)-(j-1), 2); + AirfoilXlower(j)=Airfoil(length(Airfoil)-(j-1), 1); + end + + AirfoilYupper=fliplr(AirfoilYupper); + AirfoilXupper=fliplr(AirfoilXupper); + AirfoilYlower=fliplr(AirfoilYlower); + AirfoilXlower=fliplr(AirfoilXlower); + AirfoilYlower=[0 AirfoilYlower]; + AirfoilXlower=[0 AirfoilXlower]; + + [min_diff, k]=min(abs(AirfoilX)); + + [min_diff, kU]=min(abs(AirfoilXupper-xLoc)); + [min_diff, kL]=min(abs(AirfoilXlower-xLoc)); + + if xLocwidth + lam=laminarflow; + else + lam=laminarflow-.15; + end + x=linspace(0, Chords(i,j),reso); + for k = 1:length(x) + if (k <= 100*lam) + delta_x=( 5.2 * x(k) )*(v_fps*x(k)/dynvisc)^-0.5; + wake(k,j)= delta_x; + else %if turbulent + x_tr=x(100*lam); + Re_xtr = v_fps * x_tr / dynvisc; + delta_xtr=(5.2*x_tr)*(v_fps*x(k)/dynvisc)^-(0.5); + delta_l = ((delta_xtr*((v_fps)^0.2))/(0.37*((dynvisc)^0.2)))^(1/0.8); + lt = x(k) - x_tr + delta_l; + Re_lt = v_fps * lt / dynvisc; + delta = 0.37 * lt /(Re_lt)^0.2; + wake(k,j) = delta; + end + end +wakeplot=[wakeplot, wake]; + end + +fprintf('Wake plot: %6.2f percent complete\n', 100*(i+.1*j)/((length(chords)-1)+ n*.1)) +end +wakeplot(1,:)=[]; +wakeplot(:,1)=[ ]; +flipud(wakeplot); +end +function q=finddynpress(alt, v_mach) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +%slpcuft: clugs ber cubic foot +density_slpcuft=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density_slpcuft*v_fps^2; +end diff --git a/Matlab code/tradestudyAR.m b/Matlab code/tradestudyAR.m new file mode 100755 index 0000000..865d7a3 --- /dev/null +++ b/Matlab code/tradestudyAR.m @@ -0,0 +1,123 @@ +%Master 441 Code +%all alfas in DEGREES! +%by ascorrea + +function master441() +diary +datafile=input('Input data file: \nNote: You must delete the header before using \n:','s'); +[variablenames, variablevalues]=textread(datafile, '%s %f'); + + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end +i=1; +for AR=1:.1:10 + +%CRUISE------------------------------------------------------------------] +cd0_cruise=findcd0(c_f, M_cruise, sref, swet); +cLreq_cruise=findcLrequired(alt_cruise, sref, M_cruise, weight_cruise); +alphareq_cruise=findalpharequired(cLalpha_cruise, cL0, cLreq_cruise); +cD_cruise=findcD(AR, efficiency, cd0_cruise, cLreq_cruise, cd_correction); +eloverdee_cruise=cLreq_cruise/cD_cruise; +cM_cruise=cMalpha_cruise*alphareq_cruise+cM0; + + +plotAR(i)=AR; +plotLD(i)=eloverdee_cruise; +i=i+1; +end + + +plot(plotAR, plotLD) + +fprintf('Max L/D: %f at AR: %f\n',max(plotLD), plotAR(max(plotLD)==plotLD)); + +end + +function q=findcd0(c_f, M, sref, swet) +if M>.7 +c_f=c_f*(1-.09*M^2); +end +q=c_f*(swet/sref); +end +function q=findcLalpha(AR, M, clalpha, sweep, sex, sref, doverb) +%ascorrea + +betasquared=1-M^2; +beta=sqrt(betasquared); +eta=clalpha/(2*pi/beta); +numer=2*pi*AR; +denom1=(AR^2*beta^2)/eta^2; +denom2=(tand(sweep)^2/betasquared); +denom=2+sqrt(4+denom1*(1+denom2)); +F=1.07*(1+doverb)^2; + +cLalpha=(numer/denom)*(sex/sref)*F; + +q=cLalpha; + +end +function finddragpolar(cd0, cl_alfa, cL0, sweep_LE, ar, cd_correction, filename) +alphadeg=[-12:2]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L); +plot(C_d, C_L, '.'); +title(graphname); +xlabel('C_d'); +ylabel('C_L'); +axis([0, .04, -1, 1.5]); +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end +print ('-dtiff', filename) +close(1) +end +function q=findcLrequired(alt, s, v_mach, lift) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +density=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density*v_fps^2; + +q=lift/(q*s); + +end +function q=findalpharequired(cLalpha, cL0, cLrequired) +q=(cLrequired-cL0)/cLalpha; +end +function q=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + q=cd0+cd_i+cd_correction; +end \ No newline at end of file diff --git a/Matlab code/tradestudyS.m b/Matlab code/tradestudyS.m new file mode 100755 index 0000000..c0ccc06 --- /dev/null +++ b/Matlab code/tradestudyS.m @@ -0,0 +1,124 @@ +%Master 441 Code +%all alfas in DEGREES! +%by ascorrea + +function master441() +diary +datafile=input('Input data file: \nNote: You must delete the header before using \n:','s'); +[variablenames, variablevalues]=textread(datafile, '%s %f'); + + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end +i=1; +for sref=100:100:6000 + +AR=wingspan^2/sref; +%CRUISE------------------------------------------------------------------] +cd0_cruise=findcd0(c_f, M_cruise, sref, swet); +cLreq_cruise=findcLrequired(alt_cruise, sref, M_cruise, weight_cruise); +alphareq_cruise=findalpharequired(cLalpha_cruise, cL0, cLreq_cruise); +cD_cruise=findcD(AR, efficiency, cd0_cruise, cLreq_cruise, cd_correction); +eloverdee_cruise=cLreq_cruise/cD_cruise; +cM_cruise=cMalpha_cruise*alphareq_cruise+cM0; + + +plotS(i)=sref; +plotLD(i)=eloverdee_cruise; +i=i+1; +end + + +plot(plotS, plotLD) + +fprintf('Max L/D: %f at AR: %f\n', max(plotLD), plotS(max(plotLD)==plotLD)); + +end + +function q=findcd0(c_f, M, sref, swet) +if M>.7 +c_f=c_f*(1-.09*M^2); +end +q=c_f*(swet/sref); +end +function q=findcLalpha(AR, M, clalpha, sweep, sex, sref, doverb) +%ascorrea + +betasquared=1-M^2; +beta=sqrt(betasquared); +eta=clalpha/(2*pi/beta); +numer=2*pi*AR; +denom1=(AR^2*beta^2)/eta^2; +denom2=(tand(sweep)^2/betasquared); +denom=2+sqrt(4+denom1*(1+denom2)); +F=1.07*(1+doverb)^2; + +cLalpha=(numer/denom)*(sex/sref)*F; + +q=cLalpha; + +end +function finddragpolar(cd0, cl_alfa, cL0, sweep_LE, ar, cd_correction, filename) +alphadeg=[-12:2]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L); +plot(C_d, C_L, '.'); +title(graphname); +xlabel('C_d'); +ylabel('C_L'); +axis([0, .04, -1, 1.5]); +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end +print ('-dtiff', filename) +close(1) +end +function q=findcLrequired(alt, s, v_mach, lift) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +density=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density*v_fps^2; + +q=lift/(q*s); + +end +function q=findalpharequired(cLalpha, cL0, cLrequired) +q=(cLrequired-cL0)/cLalpha; +end +function q=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + q=cd0+cd_i+cd_correction; +end \ No newline at end of file diff --git a/Matlab code/tradestudySwet.m b/Matlab code/tradestudySwet.m new file mode 100755 index 0000000..a8a06d9 --- /dev/null +++ b/Matlab code/tradestudySwet.m @@ -0,0 +1,123 @@ +%Swet Study Code +%all alfas in DEGREES! +%by ascorrea + +function tradestudySwet(datafile, desiredLD) +% datafile=input('Input data file: \nNote: You must delete the header before using \n:','s'); +[variablenames, variablevalues]=textread(datafile, '%s %f'); + + +for k = 1:length(variablenames) +eval([variablenames{k} '= variablevalues(k);']); +end +i=1; +for swet=1000:100:20000 + +AR=wingspan^2/sref; +%CRUISE------------------------------------------------------------------] +cd0_cruise=findcd0(c_f, M_cruise, sref, swet); +cLreq_cruise=findcLrequired(alt_cruise, sref, M_cruise, weight_cruise); +alphareq_cruise=findalpharequired(cLalpha_cruise, cL0, cLreq_cruise); +cD_cruise=findcD(AR, efficiency, cd0_cruise, cLreq_cruise, cd_correction); +eloverdee_cruise=cLreq_cruise/cD_cruise; +cM_cruise=cMalpha_cruise*alphareq_cruise+cM0; + + +plotSwet(i)=swet; +plotLD(i)=eloverdee_cruise; +i=i+1; +end + + +plot(plotSwet, plotLD) +[min_diff, array_pos]=min(abs(plotLD-desiredLD)); +fprintf('L/D: %f at AR: %f\n', plotLD(array_pos), plotSwet(array_pos)); + +end + +function q=findcd0(c_f, M, sref, swet) +if M>.7 +c_f=c_f*(1-.09*M^2); +end +q=c_f*(swet/sref); +end +function q=findcLalpha(AR, M, clalpha, sweep, sex, sref, doverb) +%ascorrea + +betasquared=1-M^2; +beta=sqrt(betasquared); +eta=clalpha/(2*pi/beta); +numer=2*pi*AR; +denom1=(AR^2*beta^2)/eta^2; +denom2=(tand(sweep)^2/betasquared); +denom=2+sqrt(4+denom1*(1+denom2)); +F=1.07*(1+doverb)^2; + +cLalpha=(numer/denom)*(sex/sref)*F; + +q=cLalpha; + +end +function finddragpolar(cd0, cl_alfa, cL0, sweep_LE, ar, cd_correction, filename) +alphadeg=[-12:2]; +% alpha=(pi/180)*(alphadeg); +alpha=alphadeg; +cL_alfa=cl_alfa*(ar/(ar+(2*(ar+4)/(ar+2)))); + + for i=1:length(alpha) + C_L(i)=cL_alfa*(alpha(i))+cL0; + e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i(i)=C_L(i)^2/(pi*ar*e); + C_d(i)=cd0+cd_i(i)+cd_correction; + end + + graphname='Drag Polar'; + +hold on +axisX0=linspace(0,max(cd)); +axisY0=zeros(1,length(axisX0)); +plot(axisX0, axisY0,'k--'); +plot(C_d, C_L); +plot(C_d, C_L, '.'); +title(graphname); +xlabel('C_d'); +ylabel('C_L'); +axis([0, .04, -1, 1.5]); +% for i=1:length(alphadeg) +% alphalabel=num2str(alphadeg(i)); +% label=[' \alpha =' alphalabel]; +% text(C_d(i), C_L(i), label) +% end +print ('-dtiff', filename) +close(1) +end +function q=findcLrequired(alt, s, v_mach, lift) +if alt < 36152 +temp=59-.00356*alt; +press=2116*((temp+459.7)/518.6)^5.256; + +elseif alt < 82345 + temp=-70; + press=473.1*exp(1.73-.000048*alt); + +else + print('Program Not Valid for given altitude') +end + +density=press/(1718*(temp+459.7)); +v_fps=v_mach*sqrt(1.4*1718*(temp+459.7)); +q=.5*density*v_fps^2; + +q=lift/(q*s); + +end +function q=findalpharequired(cLalpha, cL0, cLrequired) +q=(cLrequired-cL0)/cLalpha; +end +function q=findcD(ar, e, cd0, C_L, cd_correction) + +% e=4.61*(1-.045*ar^.68)*cosd(sweep_LE)^.15-3.1; + cd_i=C_L^2/(pi*ar*e); + cd_i=C_L^2/(pi*ar*e); + q=cd0+cd_i+cd_correction; +end \ No newline at end of file diff --git a/Parameter Files/FDR001.param b/Parameter Files/FDR001.param new file mode 100755 index 0000000..f49f0f4 --- /dev/null +++ b/Parameter Files/FDR001.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.137 cMalpha -.063 cM0 -0.197 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR002.param b/Parameter Files/FDR002.param new file mode 100755 index 0000000..6a2bbdb --- /dev/null +++ b/Parameter Files/FDR002.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.057 cL0 0.144 cMalpha -.066 cM0 -0.211 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR003.param b/Parameter Files/FDR003.param new file mode 100755 index 0000000..6a2bbdb --- /dev/null +++ b/Parameter Files/FDR003.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.057 cL0 0.144 cMalpha -.066 cM0 -0.211 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR004.param b/Parameter Files/FDR004.param new file mode 100755 index 0000000..da46bc2 --- /dev/null +++ b/Parameter Files/FDR004.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.142 cMalpha -.065 cM0 -0.209 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR005.param b/Parameter Files/FDR005.param new file mode 100755 index 0000000..be37bbc --- /dev/null +++ b/Parameter Files/FDR005.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.142 cMalpha -.062 cM0 -0.196 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR006.param b/Parameter Files/FDR006.param new file mode 100755 index 0000000..c19620f --- /dev/null +++ b/Parameter Files/FDR006.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.057 cL0 0.150 cMalpha -.068 cM0 -0.230 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR007.param b/Parameter Files/FDR007.param new file mode 100755 index 0000000..d3b3e21 --- /dev/null +++ b/Parameter Files/FDR007.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.058 cL0 0.150 cMalpha -.072 cM0 -0.237 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR008.param b/Parameter Files/FDR008.param new file mode 100755 index 0000000..d3b3e21 --- /dev/null +++ b/Parameter Files/FDR008.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.058 cL0 0.150 cMalpha -.072 cM0 -0.237 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR009.param b/Parameter Files/FDR009.param new file mode 100755 index 0000000..6a7598f --- /dev/null +++ b/Parameter Files/FDR009.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.053 cL0 0.136 cMalpha -.062 cM0 -0.201 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR010.param b/Parameter Files/FDR010.param new file mode 100755 index 0000000..d727138 --- /dev/null +++ b/Parameter Files/FDR010.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.052 cL0 0.170 cMalpha -.056 cM0 -0.236 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR013.param b/Parameter Files/FDR013.param new file mode 100755 index 0000000..eac25cc --- /dev/null +++ b/Parameter Files/FDR013.param @@ -0,0 +1,2 @@ +laminarflow_to .35 laminarflow_cruise .50 laminarflow_loiter .50 laminarflow_landing .35 + M_cruise 0.8 M_to 0.2509 M_loiter 0.3 M_landing 0.28 cLalpha 0.056 cL0 0.198 cMalpha -0.059 cM0 -0.267 efficiency 0.8872 efficiency_to 0.8872 efficiency_cruise 0.8872 efficiency_loiter 0.8872 efficiency_landing 0.8872 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0.0005 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/FDR020.param b/Parameter Files/FDR020.param new file mode 100755 index 0000000..d968476 --- /dev/null +++ b/Parameter Files/FDR020.param @@ -0,0 +1 @@ +laminarflow_to .35 laminarflow_cruise .50 laminarflow_loiter .50 laminarflow_landing .35 M_cruise 0.8 M_to 0.2509 M_loiter 0.3 M_landing 0.28 cLalpha 0.037 cL0 0.0845 cMalpha 0.0003 cM0 -0.0369 efficiency_to 0.7781 efficiency_cruise 0.98 efficiency_loiter 0.9692 efficiency_landing 0.8791 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 173400 weight_to 173400 weight_loiter 133900 weight_landing 133900 cd_correction 0 c_f 0.003 D_engine 240.5 fuse_width 57.96 Dragredux_BLI 5.7 sfront_landinggear 33.7 cd_landinggear .4 \ No newline at end of file diff --git a/Parameter Files/FDR020b.param b/Parameter Files/FDR020b.param new file mode 100755 index 0000000..1b49da9 --- /dev/null +++ b/Parameter Files/FDR020b.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.0514 cL0 0.1159 cMalpha 0.0000 cM0 -0.0329 efficiency_to 0.7781 efficiency_cruise 0.8561 efficiency_loiter 0.9692 efficiency_landing 0.8791 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 s_engine 200 fuse_width 57.96 \ No newline at end of file diff --git a/Parameter Files/Old Datars/FDR001.param b/Parameter Files/Old Datars/FDR001.param new file mode 100755 index 0000000..f49f0f4 --- /dev/null +++ b/Parameter Files/Old Datars/FDR001.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.137 cMalpha -.063 cM0 -0.197 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/Old Datars/FDR001.txt b/Parameter Files/Old Datars/FDR001.txt new file mode 100755 index 0000000..db92ee9 --- /dev/null +++ b/Parameter Files/Old Datars/FDR001.txt @@ -0,0 +1,15 @@ +M_cruise 0.8 +M_landing 0.2 +cLalpha_cruise 0.0559 +cLalpha_landing 0.053 +cMalpha_cruise -0.0636 +efficiency 1.016 + +alt_cruise 35000 +weight_cruise 160000 + + +cL0 0.0624 +cM0 -0.0894 +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR002.param b/Parameter Files/Old Datars/FDR002.param new file mode 100755 index 0000000..8fc2a3b --- /dev/null +++ b/Parameter Files/Old Datars/FDR002.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0571 +cL0 0.1421 +cMalpha_cruise -0.0661 +cM0 -0.2092 + +efficiency 0.8501 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR002.txt b/Parameter Files/Old Datars/FDR002.txt new file mode 100755 index 0000000..8fc2a3b --- /dev/null +++ b/Parameter Files/Old Datars/FDR002.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0571 +cL0 0.1421 +cMalpha_cruise -0.0661 +cM0 -0.2092 + +efficiency 0.8501 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR003.param b/Parameter Files/Old Datars/FDR003.param new file mode 100755 index 0000000..24438c4 --- /dev/null +++ b/Parameter Files/Old Datars/FDR003.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0572 +cL0 0.0717 +cMalpha_cruise -0.0663 +cM0 -0.106 + +efficiency 1.0089 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR003.txt b/Parameter Files/Old Datars/FDR003.txt new file mode 100755 index 0000000..24438c4 --- /dev/null +++ b/Parameter Files/Old Datars/FDR003.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0572 +cL0 0.0717 +cMalpha_cruise -0.0663 +cM0 -0.106 + +efficiency 1.0089 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR004.param b/Parameter Files/Old Datars/FDR004.param new file mode 100755 index 0000000..1d53bf5 --- /dev/null +++ b/Parameter Files/Old Datars/FDR004.param @@ -0,0 +1,15 @@ +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0566 +cL0 0.1419 +cMalpha_cruise -0.0658 +cM0 -0.2088 + +efficiency 0.8591 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR004.txt b/Parameter Files/Old Datars/FDR004.txt new file mode 100755 index 0000000..1d53bf5 --- /dev/null +++ b/Parameter Files/Old Datars/FDR004.txt @@ -0,0 +1,15 @@ +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0566 +cL0 0.1419 +cMalpha_cruise -0.0658 +cM0 -0.2088 + +efficiency 0.8591 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR005.param b/Parameter Files/Old Datars/FDR005.param new file mode 100755 index 0000000..ad26c95 --- /dev/null +++ b/Parameter Files/Old Datars/FDR005.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0567 +cL0 0.142 +cMalpha_cruise -0.062 +cM0 -0.1963 + +efficiency 0.8872 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR005.txt b/Parameter Files/Old Datars/FDR005.txt new file mode 100755 index 0000000..ad26c95 --- /dev/null +++ b/Parameter Files/Old Datars/FDR005.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0567 +cL0 0.142 +cMalpha_cruise -0.062 +cM0 -0.1963 + +efficiency 0.8872 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR006.param b/Parameter Files/Old Datars/FDR006.param new file mode 100755 index 0000000..fa4750c --- /dev/null +++ b/Parameter Files/Old Datars/FDR006.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0575 +cL0 0.1497 +cMalpha_cruise -0.0693 +cM0 -0.23 + +efficiency 0.652 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR006.txt b/Parameter Files/Old Datars/FDR006.txt new file mode 100755 index 0000000..fa4750c --- /dev/null +++ b/Parameter Files/Old Datars/FDR006.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0575 +cL0 0.1497 +cMalpha_cruise -0.0693 +cM0 -0.23 + +efficiency 0.652 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR007.param b/Parameter Files/Old Datars/FDR007.param new file mode 100755 index 0000000..afcc5ac --- /dev/null +++ b/Parameter Files/Old Datars/FDR007.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0586 +cL0 0.15 +cMalpha_cruise -0.0734 +cM0 -0.2367 + +efficiency 0.7437 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR007.txt b/Parameter Files/Old Datars/FDR007.txt new file mode 100755 index 0000000..afcc5ac --- /dev/null +++ b/Parameter Files/Old Datars/FDR007.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0586 +cL0 0.15 +cMalpha_cruise -0.0734 +cM0 -0.2367 + +efficiency 0.7437 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR008.param b/Parameter Files/Old Datars/FDR008.param new file mode 100755 index 0000000..8afa4dc --- /dev/null +++ b/Parameter Files/Old Datars/FDR008.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0586 +cL0 0.1616 +cMalpha_cruise -0.0734 +cM0 -0.2455 + +efficiency 0.8049 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR008.txt b/Parameter Files/Old Datars/FDR008.txt new file mode 100755 index 0000000..8afa4dc --- /dev/null +++ b/Parameter Files/Old Datars/FDR008.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0586 +cL0 0.1616 +cMalpha_cruise -0.0734 +cM0 -0.2455 + +efficiency 0.8049 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR009.param b/Parameter Files/Old Datars/FDR009.param new file mode 100755 index 0000000..ad6b3bf --- /dev/null +++ b/Parameter Files/Old Datars/FDR009.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.053 +cL0 0.136 +cMalpha_cruise -0.062 +cM0 -0.201 + +efficiency 0.9683 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR009.txt b/Parameter Files/Old Datars/FDR009.txt new file mode 100755 index 0000000..ad6b3bf --- /dev/null +++ b/Parameter Files/Old Datars/FDR009.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.053 +cL0 0.136 +cMalpha_cruise -0.062 +cM0 -0.201 + +efficiency 0.9683 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR010.param b/Parameter Files/Old Datars/FDR010.param new file mode 100755 index 0000000..076cfae --- /dev/null +++ b/Parameter Files/Old Datars/FDR010.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.052 +cL0 0.169 +cMalpha_cruise -0.056 +cM0 -0.236 + +efficiency 0.8049 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR010.txt b/Parameter Files/Old Datars/FDR010.txt new file mode 100755 index 0000000..076cfae --- /dev/null +++ b/Parameter Files/Old Datars/FDR010.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.052 +cL0 0.169 +cMalpha_cruise -0.056 +cM0 -0.236 + +efficiency 0.8049 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR012.param b/Parameter Files/Old Datars/FDR012.param new file mode 100755 index 0000000..b6b0116 --- /dev/null +++ b/Parameter Files/Old Datars/FDR012.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0567 +cL0 0.144 +cMalpha_cruise -0.062 +cM0 -0.199 + +efficiency 0.8872 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR012.txt b/Parameter Files/Old Datars/FDR012.txt new file mode 100755 index 0000000..b6b0116 --- /dev/null +++ b/Parameter Files/Old Datars/FDR012.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0567 +cL0 0.144 +cMalpha_cruise -0.062 +cM0 -0.199 + +efficiency 0.8872 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/FDR013.asv b/Parameter Files/Old Datars/FDR013.asv new file mode 100755 index 0000000..7110d2d --- /dev/null +++ b/Parameter Files/Old Datars/FDR013.asv @@ -0,0 +1 @@ +wingspan 160 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.0564 cL0 0.1422 cMalpha -0.0597 cM0 -0.2677 efficiency 0.775 efficiency_to 0.775 efficiency_cruise 0.8128 efficiency_loiter 0.775 efficiency_landing 0.775 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/Old Datars/FDR013.param b/Parameter Files/Old Datars/FDR013.param new file mode 100755 index 0000000..85e74d6 --- /dev/null +++ b/Parameter Files/Old Datars/FDR013.param @@ -0,0 +1 @@ +wingspan 160 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.0564 cL0 0.1422 cMalpha -0.0597 cM0 -0.2677 efficiency 0.775 efficiency_to 0.8725 efficiency_cruise 0.8128 efficiency_loiter 0.8795 efficiency_landing 0.8791 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/Old Datars/FDR013.txt b/Parameter Files/Old Datars/FDR013.txt new file mode 100755 index 0000000..d8b6047 --- /dev/null +++ b/Parameter Files/Old Datars/FDR013.txt @@ -0,0 +1,29 @@ +wingspan 160 +M_cruise 0.8 +M_to 0.2 +M_loiter 0.3 +M_landing 0.2 + +cLalpha 0.0564 +cL0 0.1422 +cMalpha -0.0597 +cM0 -0.2677 + +efficiency 0.775 +efficiency_to 0.8725 +efficiency_cruise 0.8128 +efficiency_loiter 0.8795 +efficiency_landing 0.8791 + +alt_cruise 35000 +alt_to 0 +alt_loiter 10000 +alt_landing 0 + +weight_cruise 160000 +weight_to 160000 +weight_loiter 130000 +weight_landing 130000 + +cd_correction 0 +c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/Old Datars/FDR013b.txt b/Parameter Files/Old Datars/FDR013b.txt new file mode 100755 index 0000000..8e8cc47 --- /dev/null +++ b/Parameter Files/Old Datars/FDR013b.txt @@ -0,0 +1,31 @@ +wingspan 160 +M_cruise 0.8 +M_to 0.2 +M_loiter 0.3 +M_landing 0.2 + +cLalpha 0.056 +cL0 0.198 +cMalpha -0.059 +cM0 -0.267 + + +efficiency 0.8872 +efficiency_to 0.8872 +efficiency_cruise 0.8872 +efficiency_loiter 0.8872 +efficiency_landing 0.8872 + +alt_cruise 35000 +alt_to 0 +alt_loiter 10000 +alt_landing 0 + +weight_cruise 160000 +weight_to 160000 +weight_loiter 130000 +weight_landing 130000 + + +cd_correction 0.0005 +c_f 0.003 \ No newline at end of file diff --git a/Parameter Files/Old Datars/FDR020.txt b/Parameter Files/Old Datars/FDR020.txt new file mode 100755 index 0000000..645c564 --- /dev/null +++ b/Parameter Files/Old Datars/FDR020.txt @@ -0,0 +1,35 @@ +laminarflow_to .40 +laminarflow_cruise .40 +laminarflow_loiter .40 +laminarflow_landing .40 + + +M_cruise 0.8 +M_to 0.2 +M_loiter 0.3 +M_landing 0.2 + +cLalpha 0.037 +cL0 0.0845 +cMalpha 0.0003 +cM0 -0.0369 + +efficiency_to 0.7781 +efficiency_cruise 0.8128 +efficiency_loiter 0.9692 +efficiency_landing 0.8791 + +alt_cruise 35000 +alt_to 0 +alt_loiter 10000 +alt_landing 0 + +weight_cruise 160000 +weight_to 160000 +weight_loiter 130000 +weight_landing 130000 + +cd_correction 0 +c_f 0.003 +s_engine 600 +fuse_width \ No newline at end of file diff --git a/Parameter Files/Old Datars/PDR001.param b/Parameter Files/Old Datars/PDR001.param new file mode 100755 index 0000000..60a77ce --- /dev/null +++ b/Parameter Files/Old Datars/PDR001.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0572 +cL0 0.0717 +cMalpha_cruise -0.0663 +cM0 -0.106 + +efficiency 0.7972 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Parameter Files/Old Datars/PDR001.txt b/Parameter Files/Old Datars/PDR001.txt new file mode 100755 index 0000000..60a77ce --- /dev/null +++ b/Parameter Files/Old Datars/PDR001.txt @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0572 +cL0 0.0717 +cMalpha_cruise -0.0663 +cM0 -0.106 + +efficiency 0.7972 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/Planform Constraints/FDR002.dat b/Planform Constraints/FDR002.dat new file mode 100755 index 0000000..b3f7bea --- /dev/null +++ b/Planform Constraints/FDR002.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 55 nasasc0714.dat +34.77 15 60 nasasc0714.dat +80 5 803 nasasc0714.dat diff --git a/Planform Constraints/constraint.dat b/Planform Constraints/constraint.dat new file mode 100755 index 0000000..7e17125 --- /dev/null +++ b/Planform Constraints/constraint.dat @@ -0,0 +1,4 @@ +0 54.9 10 10 +5.5 54.9 10 10 +12.88 38.9 26 10 +19.66 25.9 39 10 diff --git a/Planform Constraints/constraint10 b/Planform Constraints/constraint10 new file mode 100755 index 0000000..b343d22 --- /dev/null +++ b/Planform Constraints/constraint10 @@ -0,0 +1,4 @@ +0 65.16 12 13.33 +6.25 65.16 12 13.33 +11.4 55.83 19.917 10.5 + diff --git a/Planform Constraints/constraint2.dat b/Planform Constraints/constraint2.dat new file mode 100755 index 0000000..1114d2e --- /dev/null +++ b/Planform Constraints/constraint2.dat @@ -0,0 +1,4 @@ +0 45 20 13.33 +6.25 45 20 13.33 +12 32 33 10.5 +19.1 18 47 9.5 diff --git a/Planform Constraints/constraint2.dat~ b/Planform Constraints/constraint2.dat~ new file mode 100755 index 0000000..d907ee8 --- /dev/null +++ b/Planform Constraints/constraint2.dat~ @@ -0,0 +1,4 @@ +0 45 10 13.33 +6.25 45 10 13.33 +12 32 23 10.5 +19.1 18 37 9.5 diff --git a/Planform Constraints/constraint3.dat b/Planform Constraints/constraint3.dat new file mode 100755 index 0000000..657211d --- /dev/null +++ b/Planform Constraints/constraint3.dat @@ -0,0 +1,3 @@ +0 52 20 13.33 +6.25 52 20 13.33 +12 40 33 10.5 diff --git a/Planform Constraints/constraint4.dat b/Planform Constraints/constraint4.dat new file mode 100755 index 0000000..aeae1fc --- /dev/null +++ b/Planform Constraints/constraint4.dat @@ -0,0 +1,4 @@ +0 53.5 15 13.33 +6.25 53.5 15 13.33 +11.4 31.9 35.75 10.5 +17.5 19.25 46 9.5 diff --git a/Planform Constraints/constraint5.dat b/Planform Constraints/constraint5.dat new file mode 100755 index 0000000..adc2b48 --- /dev/null +++ b/Planform Constraints/constraint5.dat @@ -0,0 +1,4 @@ +0 58.5 15 13.33 +6.25 58.5 15 13.33 +11.4 40.91 32.58 10.5 + diff --git a/Planform Constraints/constraint6.dat b/Planform Constraints/constraint6.dat new file mode 100755 index 0000000..10588d1 --- /dev/null +++ b/Planform Constraints/constraint6.dat @@ -0,0 +1,4 @@ +0 58.5 15 13.33 +6.25 58.5 15 13.33 +11.4 43.6 29.92 10.5 + diff --git a/Planform Constraints/constraint7.asv b/Planform Constraints/constraint7.asv new file mode 100755 index 0000000..fc49175 --- /dev/null +++ b/Planform Constraints/constraint7.asv @@ -0,0 +1,4 @@ +0 58.5 15 13.33 +6.25 58.5 15 13.33 +11.4 43.6 29.92 10.5 + diff --git a/Planform Constraints/constraint7.dat b/Planform Constraints/constraint7.dat new file mode 100755 index 0000000..eb4b43b --- /dev/null +++ b/Planform Constraints/constraint7.dat @@ -0,0 +1,4 @@ +0 58.5 12 13.33 +6.25 58.5 12 13.33 +11.4 45.33 25.167 10.5 + diff --git a/Planform Constraints/constraint8 b/Planform Constraints/constraint8 new file mode 100755 index 0000000..af55869 --- /dev/null +++ b/Planform Constraints/constraint8 @@ -0,0 +1,3 @@ +0 71.75 12 13.33 +6.25 71.75 12 13.33 +11.4 55.83 19.917 10.5 \ No newline at end of file diff --git a/Planform Constraints/constraint8.asv b/Planform Constraints/constraint8.asv new file mode 100755 index 0000000..af55869 --- /dev/null +++ b/Planform Constraints/constraint8.asv @@ -0,0 +1,3 @@ +0 71.75 12 13.33 +6.25 71.75 12 13.33 +11.4 55.83 19.917 10.5 \ No newline at end of file diff --git a/Planform Constraints/constraint8.dat b/Planform Constraints/constraint8.dat new file mode 100755 index 0000000..b8dd07d --- /dev/null +++ b/Planform Constraints/constraint8.dat @@ -0,0 +1,4 @@ +0 71.75 12 13.33 +6.25 71.75 12 13.33 +11.4 55.83 19.917 10.5 + diff --git a/Planform Constraints/constraint9 b/Planform Constraints/constraint9 new file mode 100755 index 0000000..b343d22 --- /dev/null +++ b/Planform Constraints/constraint9 @@ -0,0 +1,4 @@ +0 65.16 12 13.33 +6.25 65.16 12 13.33 +11.4 55.83 19.917 10.5 + diff --git a/Planform Constraints/constraint9.dat b/Planform Constraints/constraint9.dat new file mode 100755 index 0000000..b343d22 --- /dev/null +++ b/Planform Constraints/constraint9.dat @@ -0,0 +1,4 @@ +0 65.16 12 13.33 +6.25 65.16 12 13.33 +11.4 55.83 19.917 10.5 + diff --git a/Planform Constraints/cruise.tif b/Planform Constraints/cruise.tif new file mode 100755 index 0000000..ebeacd9 Binary files /dev/null and b/Planform Constraints/cruise.tif differ diff --git a/Planforms/1996 yankees.csv b/Planforms/1996 yankees.csv new file mode 100755 index 0000000..85bf0fa --- /dev/null +++ b/Planforms/1996 yankees.csv @@ -0,0 +1 @@ +{\rtf1\ansi\ansicpg1252\cocoartf1038\cocoasubrtf250,,,,,,,,,,,,,,,,,,,,,,,,,,, {\fonttbl\f0\fmodern\fcharset0 Courier;},,,,,,,,,,,,,,,,,,,,,,,,,,, {\colortbl;\red255\green255\blue255;},,,,,,,,,,,,,,,,,,,,,,,,,,, \margl1440\margr1440\vieww9000\viewh8400\viewkind0,,,,,,,,,,,,,,,,,,,,,,,,,,, \deftab720,,,,,,,,,,,,,,,,,,,,,,,,,,, \pard\pardeftab720\ql\qnatural,,,,,,,,,,,,,,,,,,,,,,,,,,, \f0\fs26 \cf0 ,Age,B,T,Ht,,Wt,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,DH,PH,PR,Salary,\ Mike Aldrete,35,L,L,"5' 11""",5.916666667,180,Jan 29 1961,10,32,18,32,17,1,0,8,0,0,0,6,0,4,9,9,8,0,,\ Brian Boehringer,27,B,R,"6' 2""",6.166666667,180,Jan 8 1969,2,15,3,0,15,15,0,0,0,0,0,0,0,0,0,0,0,0,,\ Wade Boggs HOF,38,L,R,"6' 2""",6.166666667,190,Jun 15 1958,15,132,124,132,123,0,0,0,0,123,0,0,0,0,0,4,7,0,"$2,050,000 ",All-Star\ Ricky Bones,27,R,R,"5' 10""",5.833333333,175,Apr 7 1969,6,4,1,0,4,4,0,0,0,0,0,0,0,0,0,0,0,0,,\ Billy Brewer,28,L,L,"6' 1""",6.083333333,175,Apr 15 1968,4,4,0,0,4,4,0,0,0,0,0,0,0,0,0,0,0,0,,\ David Cone,33,L,R,"6' 1""",6.083333333,180,Jan 2 1963,11,11,11,0,11,11,0,0,0,0,0,0,0,0,0,0,0,0,"$4,666,667 ",\ Mariano Duncan,33,R,R,"6' 0""",6,160,Mar 13 1963,11,109,104,109,107,0,0,0,104,3,0,2,0,1,3,2,4,0,"$845,000 ",\ Robert Eenhoorn,28,R,R,"6' 3""",6.25,170,Feb 9 1968,3,12,4,12,12,0,0,0,10,2,0,0,0,0,0,0,0,1,"$119,000 ",\ Cecil Fielder,32,R,R,"6' 3""",6.25,230,Sep 21 1963,11,53,51,53,9,0,0,9,0,0,0,0,0,0,0,42,2,0,,\ Andy Fox,25,L,R,"6' 4""",6.333333333,205,Jan 12 1971,1st,113,50,113,105,0,0,0,72,31,9,0,0,1,1,0,4,24,"$109,000 ",\ Paul Gibson,36,R,L,"6' 0""",6,165,Jan 4 1960,8,4,0,0,4,4,0,0,0,0,0,0,0,0,0,0,0,0,,\ Joe Girardi,31,R,R,"5' 11""",5.916666667,195,Oct 14 1964,8,124,110,124,120,0,120,0,0,0,0,0,0,0,0,0,6,4,"$2,325,000 ",\ Dwight Gooden,31,R,R,"6' 2""",6.166666667,190,Nov 16 1964,12,29,29,0,29,29,0,0,0,0,0,0,0,0,0,0,0,0,"$950,000 ",\ Charlie Hayes,31,R,R,"6' 0""",6,190,May 29 1965,9,20,15,20,19,0,0,0,0,19,0,0,0,0,0,0,5,0,,\ Matt Howard,28,R,R,"5' 10""",5.833333333,165,Sep 22 1967,1st,35,14,35,34,0,0,0,30,6,0,0,0,0,0,0,3,4,,\ Steve Howe,38,L,L,"6' 1""",6.083333333,180,Mar 10 1958,12,25,0,0,25,25,0,0,0,0,0,0,0,0,0,0,0,0,"$500,000 ",\ Mark Hutton,26,R,R,"6' 6""",6.5,240,Feb 6 1970,3,12,2,0,12,12,0,0,0,0,0,0,0,0,0,0,0,0,"$119,000 ",\ Dion James,33,L,L,"6' 1""",6.083333333,170,Nov 9 1962,11,6,4,6,4,0,0,0,0,0,0,3,0,1,4,1,1,0,,\ Derek Jeter,22,R,R,"6' 3""",6.25,195,Jun 26 1974,2,157,156,157,157,0,0,0,0,0,157,0,0,0,0,0,0,0,"$130,000 ",\ Scott Kamieniecki,32,R,R,"6' 0""",6,195,Apr 19 1964,6,7,5,0,7,7,0,0,0,0,0,0,0,0,0,0,0,0,"$1,100,000 ",\ Pat Kelly,28,R,R,"6' 0""",6,180,Oct 14 1967,6,13,5,13,10,0,0,0,10,0,0,0,0,0,0,0,1,5,"$900,000 ",\ Jimmy Key,35,R,L,"6' 1""",6.083333333,185,Apr 22 1961,13,30,30,0,30,30,0,0,0,0,0,0,0,0,0,0,0,0,"$1,750,000 ",\ Jim Leyritz,32,R,R,"6' 0""",6,190,Dec 27 1963,7,88,72,88,72,0,55,5,2,13,0,3,0,0,3,10,11,0,"$1,470,000 ",\ Graeme Lloyd,29,L,L,"6' 8""",6.666666667,225,Apr 9 1967,4,13,0,0,13,13,0,0,0,0,0,0,0,0,0,0,0,0,,\ Matt Luke,25,L,L,"6' 5""",6.416666667,220,Feb 26 1971,1st,1,0,1,0,0,0,0,0,0,0,0,0,0,0,0,0,1,"$109,000 ",\ Tino Martinez,28,L,R,"6' 2""",6.166666667,205,Dec 7 1967,7,155,152,155,151,0,0,151,0,0,0,0,0,0,0,3,3,0,"$2,300,000 ",\ Tim McIntosh,31,R,R,"5' 11""",5.916666667,195,Mar 21 1965,5,3,1,3,3,0,1,1,0,1,0,0,0,0,0,0,0,0,,\ Jim Mecir,26,B,R,"6' 1""",6.083333333,195,May 16 1970,2,26,0,0,26,26,0,0,0,0,0,0,0,0,0,0,0,0,,\ Ramiro Mendoza,24,R,R,"6' 2""",6.166666667,154,Jun 15 1972,1st,12,11,0,12,12,0,0,0,0,0,0,0,0,0,0,0,0,,\ Jeff Nelson,29,R,R,"6' 8""",6.666666667,225,Nov 17 1966,5,73,0,0,73,73,0,0,0,0,0,0,0,0,0,0,0,0,"$860,000 ",\ Paul O'Neill,33,L,L,"6' 4""",6.333333333,200,Feb 25 1963,12,150,148,150,146,0,0,1,0,0,0,0,0,146,146,2,2,0,"$5,300,000 ",\ Dave Pavlas,33,R,R,"6' 7""",6.583333333,180,Aug 12 1962,4,16,0,0,16,16,0,0,0,0,0,0,0,0,0,0,0,0,"$120,000 ",\ Andy Pettitte,24,L,L,"6' 5""",6.416666667,225,Jun 15 1972,2,35,34,0,35,35,0,0,0,0,0,0,0,0,0,0,0,0,"$195,000 ",All-Star\ Dale Polley,30,R,L,"6' 0""",6,165,Aug 9 1965,1st,32,0,0,32,32,0,0,0,0,0,0,0,0,0,0,0,0,"$109,000 ",\ Jorge Posada,24,B,R,"6' 2""",6.166666667,205,Aug 17 1971,2,8,2,8,4,0,4,0,0,0,0,0,0,0,0,0,3,1,,\ Tim Raines,36,B,R,"5' 8""",5.666666667,160,Sep 16 1959,18,59,49,59,51,0,0,0,0,0,0,51,0,0,51,2,8,1,"$2,100,000 ",\ Mariano Rivera,26,R,R,"6' 2""",6.166666667,185,Nov 29 1969,2,61,0,0,61,61,0,0,0,0,0,0,0,0,0,0,0,0,"$131,125 ",\ Ruben Rivera,22,R,R,"6' 3""",6.25,200,Nov 14 1973,2,46,21,46,45,0,0,0,0,0,0,13,14,19,45,0,3,10,"$109,000 ",\ Kenny Rogers,31,L,L,"6' 1""",6.083333333,190,Nov 10 1964,8,30,30,0,30,30,0,0,0,0,0,0,0,0,0,0,0,0,"$5,000,000 ",\ Ruben Sierra,30,B,R,"6' 1""",6.083333333,220,Oct 6 1965,11,96,93,96,33,0,0,0,0,0,0,32,0,1,33,60,3,0,"$6,200,000 ",\ Luis Sojo,31,R,R,"5' 11""",5.916666667,172,Jan 3 1965,7,18,11,18,17,0,0,0,14,1,4,0,0,0,0,0,1,0,,\ Darryl Strawberry,34,L,L,"6' 6""",6.5,190,Mar 12 1962,14,63,55,63,34,0,0,0,0,0,0,26,0,8,34,24,8,0,"$300,000 ",\ David Weathers,26,R,R,"6' 3""",6.25,235,Sep 25 1969,6,11,4,0,11,11,0,0,0,0,0,0,0,0,0,0,0,0,,\ John Wetteland,29,R,R,"6' 2""",6.166666667,195,Aug 21 1966,8,62,0,1,62,62,0,0,0,0,0,0,0,0,0,0,0,0,"$4,000,000 ",All-Star\ Wally Whitehurst,32,R,R,"6' 3""",6.25,180,Apr 11 1964,7,2,2,0,2,2,0,0,0,0,0,0,0,0,0,0,0,0,"$125,000 ",\ Bob Wickman,27,R,R,"6' 1""",6.083333333,240,Feb 6 1969,5,58,0,0,58,58,0,0,0,0,0,0,0,0,0,0,0,0,"$850,000 ",\ Bernie Williams,27,B,R,"6' 2""",6.166666667,180,Sep 13 1968,6,143,142,143,140,0,0,0,0,0,0,0,140,0,140,2,1,0,"$3,000,000 ",\ Gerald Williams,29,R,R,"6' 2""",6.166666667,190,Aug 10 1966,5,99,57,99,93,0,0,0,0,0,0,70,14,10,93,1,8,11,"$200,000 ",\ ,Age,B,T,Ht,6.152777778,192,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,DH,PH,PR,Salary,} ,,,,,1.83333336,,,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/Planforms/2009 yankees.csv b/Planforms/2009 yankees.csv new file mode 100755 index 0000000..4400518 --- /dev/null +++ b/Planforms/2009 yankees.csv @@ -0,0 +1 @@ +{\rtf1\ansi\ansicpg1252\cocoartf1038\cocoasubrtf250,,,,,,,,,,,,,,,,,,,,,,,,,,, {\fonttbl\f0\fswiss\fcharset0 Helvetica;},,,,,,,,,,,,,,,,,,,,,,,,,,, {\colortbl;\red255\green255\blue255;},,,,,,,,,,,,,,,,,,,,,,,,,,, \margl1440\margr1440\vieww9000\viewh8400\viewkind0,,,,,,,,,,,,,,,,,,,,,,,,,,, \pard\tx720\tx1440\tx2160\tx2880\tx3600\tx4320\tx5040\tx5760\tx6480\tx7200\tx7920\tx8640\ql\qnatural\pardirnatural,,,,,,,,,,,,,,,,,,,,,,,,,,, \f0\fs24 \cf0 ,Age,B,T,Ht,,Wt,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,DH,PH,PR,Salary,\ Alfredo Aceves,26,R,R,"6' 3""",6.25,220,Dec 8 1982,2,43,1,3,43,43,0,0,0,0,0,0,0,0,0,0,0,0,,\ Jonathan Albaladejo,26,R,R,"6' 5""",6.416666667,260,Oct 30 1982,3,32,0,1,32,32,0,0,0,0,0,0,0,0,0,0,0,0,"$403,075 ",\ Angel Berroa,29,R,R,"6' 0""",6,195,Jan 27 1980,9,21,6,21,16,0,0,0,0,16,0,0,0,0,0,0,1,7,,\ Brian Bruney,27,R,R,"6' 3""",6.25,245,Feb 17 1982,6,44,0,6,44,44,0,0,0,0,0,0,0,0,0,0,0,0,"$1,250,000 ",\ A.J. Burnett,32,R,R,"6' 4""",6.333333333,230,Jan 3 1977,11,33,33,2,33,33,0,0,0,0,0,0,0,0,0,0,0,0,"$16,500,000 ",\ Melky Cabrera,24,B,L,"5' 11""",5.916666667,200,Aug 11 1984,5,154,130,154,151,0,0,0,0,0,0,40,103,48,151,0,7,2,"$1,400,000 ",\ Robinson Cano,26,L,R,"6' 0""",6,205,Oct 22 1982,5,161,158,161,161,0,0,0,161,0,0,0,0,0,0,0,2,0,"$6,000,000 ",\ Kevin Cash,31,R,R,"6' 0""",6,190,Dec 6 1977,7,10,7,10,10,0,10,0,0,0,0,0,0,0,0,0,0,0,,\ Francisco Cervelli,23,R,R,"6' 1""",6.083333333,170,Mar 6 1986,2,42,25,42,40,0,40,0,0,0,0,0,0,0,0,0,1,1,,\ Joba Chamberlain,23,R,R,"6' 2""",6.166666667,230,Sep 23 1985,3,32,31,1,32,32,0,0,0,0,0,0,0,0,0,0,0,0,"$432,575 ",\ Anthony Claggett,24,B,R,"6' 3""",6.25,195,Jul 15 1984,1st,2,0,0,2,2,0,0,0,0,0,0,0,0,0,0,0,0,,\ Phil Coke,26,L,L,"6' 1""",6.083333333,210,Jul 19 1982,2,72,0,8,72,72,0,0,0,0,0,0,0,0,0,0,0,0,"$403,300 ",\ Johnny Damon,35,L,L,"6' 2""",6.166666667,205,Nov 5 1973,15,143,133,143,133,0,0,0,0,0,0,133,0,0,133,4,8,0,"$13,000,000 ",\ Shelley Duncan,29,R,R,"6' 5""",6.416666667,215,Sep 29 1979,3,11,3,11,8,0,0,0,0,0,0,0,0,8,8,1,3,2,,\ Michael Dunn,24,L,L,"6' 1""",6.083333333,195,May 23 1985,1st,4,0,0,4,4,0,0,0,0,0,0,0,0,0,0,0,0,,\ Brett Gardner,25,L,L,"5' 10""",5.833333333,180,Aug 24 1983,2,108,63,108,99,0,0,0,0,0,0,0,99,0,99,0,6,11,"$414,000 ",\ Chad Gaudin,26,R,R,"5' 10""",5.833333333,180,Mar 24 1983,7,11,6,1,11,11,0,0,0,0,0,0,0,0,0,0,0,0,,\ Freddy Guzman,28,B,R,"5' 10""",5.833333333,165,Jan 20 1981,4,10,0,10,7,0,0,0,0,0,0,5,0,3,7,0,1,8,,\ Jerry Hairston,33,R,R,"5' 10""",5.833333333,185,May 29 1976,12,45,21,45,41,0,0,0,3,16,11,10,2,9,19,0,4,8,,\ Eric Hinske,31,L,R,"6' 2""",6.166666667,235,Aug 5 1977,8,39,19,39,33,0,0,0,0,10,0,2,0,22,24,1,9,1,,\ Phil Hughes,23,R,R,"6' 5""",6.416666667,220,Jun 24 1986,3,51,7,7,51,51,0,0,0,0,0,0,0,0,0,0,0,0,,\ Derek Jeter,35,R,R,"6' 3""",6.25,195,Jun 26 1974,15,153,152,153,150,0,0,0,0,0,150,0,0,0,0,5,1,0,"$21,600,000 ",All-Star\ Ian Kennedy,24,R,R,"6' 0""",6,195,Dec 19 1984,3,1,0,0,1,1,0,0,0,0,0,0,0,0,0,0,0,0,,\ Damaso Marte,34,L,L,"6' 2""",6.166666667,210,Feb 14 1975,10,21,0,0,21,21,0,0,0,0,0,0,0,0,0,0,0,0,"$3,750,000 ",\ Hideki Matsui,35,L,R,"6' 2""",6.166666667,210,Jun 12 1974,7,142,116,142,0,0,0,0,0,0,0,0,0,0,0,116,26,0,"$13,000,000 ",\ Mark Melancon,24,R,R,"6' 2""",6.166666667,215,Mar 28 1985,1st,13,0,1,13,13,0,0,0,0,0,0,0,0,0,0,0,0,,\ Juan Miranda,26,L,L,"6' 0""",6,220,Apr 25 1983,2,8,1,8,8,0,0,8,0,0,0,0,0,0,0,0,1,1,,\ Sergio Mitre,28,R,R,"6' 3""",6.25,225,Feb 16 1981,6,12,9,0,12,12,0,0,0,0,0,0,0,0,0,0,0,0,,\ Jose Molina,34,R,R,"6' 2""",6.166666667,245,Jun 3 1975,10,52,43,52,51,0,49,3,0,1,0,0,0,0,0,1,1,0,"$2,125,000 ",\ Xavier Nady,30,R,R,"6' 2""",6.166666667,210,Nov 14 1978,8,7,7,7,6,0,0,0,0,0,0,0,0,6,6,1,0,0,"$6,550,000 ",\ Ramiro Pena,23,B,R,"5' 11""",5.916666667,165,Jul 18 1985,1st,69,28,69,61,0,0,0,8,27,34,0,0,0,0,0,3,14,"$400,000 ",\ Andy Pettitte,37,L,L,"6' 5""",6.416666667,225,Jun 15 1972,15,32,32,2,32,32,0,0,0,0,0,0,0,0,0,0,0,0,"$5,500,000 ",\ Jorge Posada,37,B,R,"6' 2""",6.166666667,205,Aug 17 1971,15,111,97,111,100,0,100,2,0,0,0,0,0,0,0,9,14,0,"$13,100,000 ",\ Edwar Ramirez,28,R,R,"6' 3""",6.25,150,Mar 28 1981,3,20,0,0,20,20,0,0,0,0,0,0,0,0,0,0,0,0,"$422,450 ",\ Cody Ransom,33,R,R,"6' 2""",6.166666667,205,Feb 17 1976,7,31,22,31,28,0,0,1,1,23,3,0,0,0,0,0,0,6,"$455,100 ",\ Mariano Rivera,39,R,R,"6' 2""",6.166666667,185,Nov 29 1969,15,66,0,6,66,66,0,0,0,0,0,0,0,0,0,0,0,0,"$15,000,000 ",All-Star\ David Robertson,24,R,R,"5' 11""",5.916666667,180,Apr 9 1985,2,45,0,6,45,45,0,0,0,0,0,0,0,0,0,0,0,0,,\ Alex Rodriguez,33,R,R,"6' 3""",6.25,225,Jul 27 1975,16,124,122,124,116,0,0,0,0,116,0,0,0,0,0,9,2,0,"$33,000,000 ",\ CC Sabathia,28,L,L,"6' 7""",6.583333333,290,Jul 21 1980,9,34,34,2,34,34,0,0,0,0,0,0,0,0,0,0,0,0,"$15,285,714 ",\ Nick Swisher,28,B,L,"6' 0""",6,215,Nov 25 1980,6,150,141,150,144,1,0,20,0,0,0,8,0,130,134,1,6,0,"$5,400,000 ",\ Mark Teixeira,29,B,R,"6' 3""",6.25,220,Apr 11 1980,7,156,155,156,152,0,0,152,0,0,0,0,0,0,0,5,1,0,"$20,625,000 ",All-Star\ Brett Tomko,36,R,R,"6' 1""",6.083333333,220,Apr 7 1973,13,15,0,3,15,15,0,0,0,0,0,0,0,0,0,0,0,0,,\ Josh Towers,32,R,R,"6' 1""",6.083333333,190,Feb 26 1977,8,2,0,0,2,2,0,0,0,0,0,0,0,0,0,0,0,0,,\ Jose Veras,28,R,R,"6' 5""",6.416666667,235,Oct 20 1980,4,25,0,0,25,25,0,0,0,0,0,0,0,0,0,0,0,0,"$432,975 ",\ Chien-Ming Wang,29,R,R,"6' 3""",6.25,225,Mar 31 1980,5,12,9,2,12,12,0,0,0,0,0,0,0,0,0,0,0,0,"$5,000,000 ",\ ,Age,B,T,Ht,6.146296296,208.6666667,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,DH,PH,PR,Salary,\ },,,,,,,,,,,,,,,,,,,,,,,,,,, ,,,,,1.7555556,,,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/Planforms/27 yankees.csv b/Planforms/27 yankees.csv new file mode 100755 index 0000000..a752ddb --- /dev/null +++ b/Planforms/27 yankees.csv @@ -0,0 +1 @@ +{\rtf1\ansi\ansicpg1252\cocoartf1038\cocoasubrtf250,,,,,,,,,,,,,,,,,,,,,,,, {\fonttbl\f0\fmodern\fcharset0 Courier;},,,,,,,,,,,,,,,,,,,,,,,, {\colortbl;\red255\green255\blue255;},,,,,,,,,,,,,,,,,,,,,,,, \margl1440\margr1440\vieww9000\viewh8400\viewkind0,,,,,,,,,,,,,,,,,,,,,,,, \deftab720,,,,,,,,,,,,,,,,,,,,,,,, \pard\pardeftab720\ql\qnatural,,,,,,,,,,,,,,,,,,,,,,,, \f0\fs26 \cf0 ,Age,B,T,Ht,,Wt,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,PH,PR\ Walter Beall,27,R,R,"5' 10""",5.833333333,178,Jul 29 1899,4,1,,1,1,1,0,0,0,0,0,0,0,0,0,,\ Benny Bengough,28,R,R,"5' 7""",5.583333333,168,Jul 27 1898,5,31,,31,31,0,30,0,0,0,0,0,0,0,0,,\ Pat Collins,30,R,R,"5' 11""",5.916666667,178,Sep 13 1896,8,92,,92,92,0,89,0,0,0,0,0,0,0,0,,\ Earle Combs HOF,28,L,R,"6' 0""",6,185,May 14 1899,4,152,,152,152,0,0,0,0,0,0,0,152,0,152,,\ Joe Dugan,30,R,R,"5' 11""",5.916666667,160,May 12 1897,11,112,,112,112,0,0,0,0,111,0,0,0,0,0,,\ Cedric Durst,30,L,L,"5' 11""",5.916666667,160,Aug 23 1896,4,65,,65,65,0,0,2,0,0,0,13,6,17,36,,\ Mike Gazella,31,R,R,"5' 7""",5.583333333,165,Oct 13 1895,3,54,,54,54,0,0,0,0,44,6,0,0,0,0,,\ Lou Gehrig HOF,24,L,L,"6' 0""",6,200,Jun 19 1903,5,155,,155,155,0,0,155,0,0,0,0,0,0,0,,\ Joe Giard,28,L,L,"5' 10""",5.833333333,170,Oct 7 1898,3,16,,16,16,16,0,0,0,0,0,0,0,0,0,,\ Johnny Grabowski,27,R,R,"5' 10""",5.833333333,185,Jan 7 1900,4,70,,70,70,0,68,0,0,0,0,0,0,0,0,,\ Waite Hoyt HOF,27,R,R,"6' 0""",6,180,Sep 9 1899,10,36,,36,36,36,0,0,0,0,0,0,0,0,0,,\ Mark Koenig,22,B,R,"6' 0""",6,180,Jul 19 1904,3,123,,123,123,0,0,0,0,0,122,0,0,0,0,,\ Tony Lazzeri HOF,23,R,R,"5' 11""",5.916666667,170,Dec 6 1903,2,153,,153,153,0,0,0,113,9,38,0,0,0,0,,\ Bob Meusel,30,R,R,"6' 3""",6.25,190,Jul 19 1896,8,135,,135,135,0,0,0,0,0,0,83,0,48,131,,\ Wilcy Moore,30,R,R,"6' 0""",6,195,May 20 1897,1st,50,,50,50,50,0,0,0,0,0,0,0,0,0,,\ Ray Morehart,27,L,R,"5' 9""",5.75,157,Dec 2 1899,3,73,,73,73,0,0,0,53,0,0,0,0,0,0,,\ Ben Paschal,31,R,R,"5' 11""",5.916666667,185,Oct 13 1895,6,50,,50,50,0,0,0,0,0,0,11,4,12,27,,\ Herb Pennock HOF,33,B,L,"6' 0""",6,160,Feb 10 1894,15,34,,34,34,34,0,0,0,0,0,0,0,0,0,,\ George Pipgras,27,R,R,"6' 1""",6.083333333,185,Dec 20 1899,3,29,,29,29,29,0,0,0,0,0,0,0,0,0,,\ Dutch Ruether,33,L,L,"6' 1""",6.083333333,180,Sep 13 1893,11,35,,35,35,27,0,0,0,0,0,0,0,0,0,,\ Babe Ruth HOF,32,L,L,"6' 2""",6.166666667,215,Feb 6 1895,14,151,,151,151,0,0,0,0,0,0,56,0,95,151,,\ Bob Shawkey,36,R,R,"5' 11""",5.916666667,168,Dec 4 1890,15,19,,19,19,19,0,0,0,0,0,0,0,0,0,,\ Urban Shocker,36,R,R,"5' 10""",5.833333333,170,Sep 22 1890,12,31,,31,31,31,0,0,0,0,0,0,0,0,0,,\ Myles Thomas,29,R,R,"5' 9""",5.75,170,Oct 22 1897,2,21,,21,21,21,0,0,0,0,0,0,0,0,0,,\ Julie Wera,25,R,R,"5' 8""",5.666666667,164,Feb 9 1902,1st,38,,38,38,0,0,0,0,19,0,0,0,0,0,,\ ,Age,B,T,Ht,5.91,176.72,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,PH,PR\ },,,,,,,,,,,,,,,,,,,,,,,, ,,,,,10.92,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/Planforms/61 yankees.csv b/Planforms/61 yankees.csv new file mode 100755 index 0000000..f8d214a --- /dev/null +++ b/Planforms/61 yankees.csv @@ -0,0 +1 @@ +{\rtf1\ansi\ansicpg1252\cocoartf1038\cocoasubrtf250,,,,,,,,,,,,,,,,,,,,,,,,, {\fonttbl\f0\fmodern\fcharset0 Courier;},,,,,,,,,,,,,,,,,,,,,,,,, {\colortbl;\red255\green255\blue255;},,,,,,,,,,,,,,,,,,,,,,,,, \margl1440\margr1440\vieww9000\viewh8400\viewkind0,,,,,,,,,,,,,,,,,,,,,,,,, \deftab720,,,,,,,,,,,,,,,,,,,,,,,,, \pard\pardeftab720\ql\qnatural,,,,,,,,,,,,,,,,,,,,,,,,, \f0\fs26 \cf0 ,Age,B,T,Ht,,Wt,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,PH,PR,\ Luis Arroyo,34,L,L,"5' 8""",5.666666667,178,Feb 18 1927,6,65,0,65,65,65,0,0,0,0,0,0,0,0,0,0,0,All-Star\ Yogi Berra HOF,36,L,R,"5' 7""",5.583333333,185,May 12 1925,16,119,98,119,101,0,15,0,0,0,0,81,0,8,87,20,0,All-Star\ Johnny Blanchard,28,L,R,"6' 1""",6.083333333,193,Feb 26 1933,4,93,54,93,62,0,48,0,0,0,0,8,0,7,15,33,0,\ Clete Boyer,24,R,R,"6' 0""",6,165,Feb 9 1937,6,148,146,148,148,0,0,0,0,141,12,0,0,0,0,0,0,\ Bob Cerv,35,R,R,"6' 0""",6,200,May 5 1926,11,57,27,57,33,0,0,3,0,0,0,28,2,0,30,25,1,\ Tex Clevenger,28,R,R,"6' 1""",6.083333333,180,Jul 9 1932,7,21,0,21,21,21,0,0,0,0,0,0,0,0,0,0,0,\ Jim Coates,28,R,R,"6' 4""",6.333333333,192,Aug 4 1932,4,43,11,43,43,43,0,0,0,0,0,0,0,0,0,0,0,\ Bud Daley,28,L,L,"6' 1""",6.083333333,185,Oct 7 1932,7,23,17,23,23,23,0,0,0,0,0,0,0,0,0,0,0,\ Joe DeMaestri,32,R,R,"6' 0""",6,170,Dec 9 1928,11,30,9,30,27,0,0,0,5,4,18,0,0,0,0,0,3,\ Art Ditmar,32,R,R,"6' 2""",6.166666667,185,Apr 3 1929,8,12,8,12,12,12,0,0,0,0,0,0,0,0,0,0,0,\ Al Downing,20,R,L,"5' 11""",5.916666667,175,Jun 28 1941,1st,5,1,5,5,5,0,0,0,0,0,0,0,0,0,0,0,\ Ryne Duren,32,R,R,"6' 2""",6.166666667,190,Feb 22 1929,6,4,0,4,4,4,0,0,0,0,0,0,0,0,0,0,0,\ Whitey Ford HOF,34,L,L,"5' 10""",5.833333333,178,Oct 21 1926,10,39,39,39,39,39,0,0,0,0,0,0,0,0,0,0,0,All-Star\ Billy Gardner,33,R,R,"6' 0""",6,170,Jul 19 1927,8,41,25,41,37,0,0,0,6,33,0,0,0,0,0,3,7,\ Jesse Gonder,25,L,R,"5' 10""",5.833333333,180,Jan 20 1936,2,15,0,15,0,0,0,0,0,0,0,0,0,0,0,15,0,\ Bob Hale,27,L,L,"5' 10""",5.833333333,195,Nov 7 1933,7,11,1,11,3,0,0,3,0,0,0,0,0,0,0,8,0,\ Elston Howard,32,R,R,"6' 2""",6.166666667,196,Feb 23 1929,7,129,115,129,120,0,111,9,0,0,0,0,0,0,0,14,0,All-Star\ Johnny James,27,L,R,"5' 10""",5.833333333,160,Jul 23 1933,3,1,0,1,1,1,0,0,0,0,0,0,0,0,0,0,0,\ Deron Johnson,22,R,R,"6' 2""",6.166666667,200,Jul 17 1938,2,13,3,13,8,0,0,0,0,8,0,0,0,0,0,5,0,\ Tony Kubek,25,L,R,"6' 3""",6.25,190,Oct 12 1935,5,153,145,153,145,0,0,0,0,0,145,0,0,0,0,8,0,All-Star\ Hector Lopez,31,R,R,"5' 11""",5.916666667,182,Jul 8 1929,7,93,58,93,72,0,0,0,0,0,0,65,0,9,72,22,3,\ Duke Maas,32,R,R,"5' 10""",5.833333333,170,Jan 31 1929,7,1,0,1,1,1,0,0,0,0,0,0,0,0,0,0,0,\ Mickey Mantle HOF,29,B,R,"5' 11""",5.916666667,195,Oct 20 1931,11,153,149,153,150,0,0,0,0,0,0,0,150,0,150,3,0,All-Star\ Roger Maris,26,L,R,"6' 0""",6,197,Sep 10 1934,5,161,160,161,160,0,0,0,0,0,0,0,17,150,160,1,0,All-Star\ Danny McDevitt,28,L,L,"5' 10""",5.833333333,175,Nov 18 1932,5,8,2,8,8,8,0,0,0,0,0,0,0,0,0,0,0,\ Jack Reed,28,R,R,"6' 0""",6,185,Feb 2 1933,1st,28,3,28,27,0,0,0,0,0,0,12,14,1,27,0,7,\ Hal Reniff,22,R,R,"6' 0""",6,215,Jul 2 1938,1st,25,0,25,25,25,0,0,0,0,0,0,0,0,0,0,0,\ Bobby Richardson,25,R,R,"5' 9""",5.75,170,Aug 19 1935,7,162,160,162,161,0,0,0,161,0,0,0,0,0,0,1,0,\ Rollie Sheldon,24,R,R,"6' 4""",6.333333333,185,Dec 17 1936,1st,36,21,36,35,35,0,0,0,0,0,0,0,0,0,0,1,\ Bill Skowron,30,R,R,"5' 11""",5.916666667,195,Dec 18 1930,8,150,147,150,149,0,0,149,0,0,0,0,0,0,0,1,0,All-Star\ Bill Stafford,21,R,R,"6' 1""",6.083333333,188,Aug 13 1939,2,36,25,36,36,36,0,0,0,0,0,0,0,0,0,0,0,\ Ralph Terry,25,R,R,"6' 3""",6.25,195,Jan 9 1936,6,31,27,31,31,31,0,0,0,0,0,0,0,0,0,0,0,\ Lee Thomas,25,L,L,"6' 2""",6.166666667,195,Feb 5 1936,1st,2,0,2,0,0,0,0,0,0,0,0,0,0,0,2,0,\ Earl Torgeson,37,L,L,"6' 3""",6.25,180,Jan 1 1924,15,22,3,22,8,0,0,8,0,0,0,0,0,0,0,11,3,\ Tom Tresh,22,B,R,"6' 1""",6.083333333,180,Sep 20 1938,1st,9,1,9,3,0,0,0,0,0,3,0,0,0,0,3,3,\ Bob Turley,30,R,R,"6' 2""",6.166666667,215,Sep 19 1930,10,15,12,15,15,15,0,0,0,0,0,0,0,0,0,0,0,\ ,Age,B,T,Ht,6.013888889,185.8055556,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,PH,PR,} ,,,,,0.1666668,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/Planforms/78 yankees.csv b/Planforms/78 yankees.csv new file mode 100755 index 0000000..e78b344 --- /dev/null +++ b/Planforms/78 yankees.csv @@ -0,0 +1 @@ +{\rtf1\ansi\ansicpg1252\cocoartf1038\cocoasubrtf250,,,,,,,,,,,,,,,,,,,,,,,,,, {\fonttbl\f0\fmodern\fcharset0 Courier;},,,,,,,,,,,,,,,,,,,,,,,,,, {\colortbl;\red255\green255\blue255;},,,,,,,,,,,,,,,,,,,,,,,,,, \margl1440\margr1440\vieww9000\viewh8400\viewkind0,,,,,,,,,,,,,,,,,,,,,,,,,, \deftab720,,,,,,,,,,,,,,,,,,,,,,,,,, \pard\pardeftab720\ql\qnatural,,,,,,,,,,,,,,,,,,,,,,,,,, \f0\fs26 \cf0 ,Age,B,T,Ht,,Wt,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,DH,PH,PR,\ Dell Alston,25,L,R,"6' 0""",6,180,Sep 22 1952,2,3,0,3,0,0,0,0,0,0,0,0,0,0,0,0,3,0,\ Jim Beattie,23,R,R,"6' 5""",6.416666667,210,Jul 4 1954,1st,25,22,0,25,25,0,0,0,0,0,0,0,0,0,0,0,0,\ Paul Blair,34,R,R,"6' 0""",6,168,Feb 1 1944,15,75,20,75,71,0,0,0,5,3,4,1,49,16,64,0,16,7,\ Chris Chambliss,29,L,R,"6' 1""",6.083333333,195,Dec 26 1948,8,162,161,162,155,0,0,155,0,0,0,0,0,0,0,7,1,0,\ Ken Clay,24,R,R,"6' 3""",6.25,185,Apr 6 1954,2,28,6,1,28,28,0,0,0,0,0,0,0,0,0,0,0,0,\ Ron Davis,22,R,R,"6' 4""",6.333333333,205,Aug 6 1955,1st,4,0,0,4,4,0,0,0,0,0,0,0,0,0,0,0,0,\ Bucky Dent,26,R,R,"5' 9""",5.75,170,Nov 25 1951,6,123,120,123,123,0,0,0,0,0,123,0,0,0,0,0,0,0,\ Brian Doyle,23,L,R,"5' 10""",5.833333333,160,Jan 26 1955,1st,39,14,39,38,0,0,0,29,5,7,0,0,0,0,0,1,5,\ Rawly Eastwick,27,R,R,"6' 3""",6.25,180,Oct 24 1950,5,8,0,0,8,8,0,0,0,0,0,0,0,0,0,0,0,0,\ Ed Figueroa,29,R,R,"6' 1""",6.083333333,190,Oct 14 1948,5,35,35,1,35,35,0,0,0,0,0,0,0,0,0,0,0,0,\ Damaso Garcia,21,R,R,"6' 1""",6.083333333,165,Feb 7 1957,1st,18,14,18,18,0,0,0,16,0,3,0,0,0,0,0,0,0,\ Rich Gossage HOF,26,R,R,"6' 3""",6.25,180,Jul 5 1951,7,63,0,0,63,63,0,0,0,0,0,0,0,0,0,0,0,0,All-Star\ Ron Guidry,27,L,L,"5' 11""",5.916666667,161,Aug 28 1950,4,37,35,2,35,35,0,0,0,0,0,0,0,0,0,0,0,2,All-Star\ Don Gullett,27,R,L,"6' 0""",6,190,Jan 6 1951,9,8,8,0,8,8,0,0,0,0,0,0,0,0,0,0,0,0,\ Fran Healy,31,R,R,"6' 5""",6.416666667,220,Sep 6 1946,9,1,0,1,1,0,1,0,0,0,0,0,0,0,0,0,0,0,\ Mike Heath,23,R,R,"5' 11""",5.916666667,180,Feb 5 1955,1st,33,24,33,33,0,33,0,0,0,0,0,0,0,0,0,0,1,\ Ken Holtzman,32,R,L,"6' 2""",6.166666667,175,Nov 3 1945,14,5,3,0,5,5,0,0,0,0,0,0,0,0,0,0,0,0,\ Catfish Hunter HOF,32,R,R,"6' 0""",6,190,Apr 8 1946,14,21,20,0,21,21,0,0,0,0,0,0,0,0,0,0,0,0,\ Reggie Jackson HOF,32,L,L,"6' 0""",6,195,May 18 1946,12,139,138,139,104,0,0,0,0,0,0,0,0,104,104,34,1,0,All-Star\ Cliff Johnson,30,R,R,"6' 4""",6.333333333,215,Jul 22 1947,7,76,46,76,23,0,22,1,0,0,0,0,0,0,0,32,22,0,\ Jay Johnstone,32,L,R,"6' 1""",6.083333333,175,Nov 20 1945,13,36,16,36,22,0,0,0,0,0,0,8,0,14,22,4,9,2,\ Bob Kammeyer,27,R,R,"6' 4""",6.333333333,210,Dec 2 1950,1st,7,0,0,7,7,0,0,0,0,0,0,0,0,0,0,0,0,\ Mickey Klutts,23,R,R,"5' 11""",5.916666667,170,Sep 20 1954,3,1,1,1,1,0,0,0,0,1,0,0,0,0,0,0,0,0,\ Paul Lindblad,36,L,L,"6' 1""",6.083333333,185,Aug 9 1941,14,7,1,0,7,7,0,0,0,0,0,0,0,0,0,0,0,0,\ Sparky Lyle,33,L,L,"6' 1""",6.083333333,182,Jul 22 1944,12,59,0,0,59,59,0,0,0,0,0,0,0,0,0,0,0,0,\ Larry McCall,25,L,R,"6' 2""",6.166666667,195,Sep 8 1952,2,5,1,0,5,5,0,0,0,0,0,0,0,0,0,0,0,0,\ Andy Messersmith,32,R,R,"6' 1""",6.083333333,200,Aug 6 1945,11,6,5,0,6,6,0,0,0,0,0,0,0,0,0,0,0,0,\ Thurman Munson,31,R,R,"5' 11""",5.916666667,190,Jun 7 1947,10,154,153,154,139,0,126,0,0,0,0,0,0,13,13,14,1,0,All-Star\ Graig Nettles,33,L,R,"6' 0""",6,180,Aug 20 1944,12,159,159,159,159,0,0,0,0,159,2,0,0,0,0,0,0,0,All-Star\ Lou Piniella,34,R,R,"6' 0""",6,182,Aug 28 1943,12,130,120,130,103,0,0,0,0,0,0,80,0,26,103,19,10,0,\ Dave Rajsich,26,L,L,"6' 5""",6.416666667,175,Sep 28 1951,1st,4,2,0,4,4,0,0,0,0,0,0,0,0,0,0,0,0,\ Domingo Ramos,20,R,R,"5' 10""",5.833333333,154,Mar 29 1958,1st,1,0,1,1,0,0,0,0,0,1,0,0,0,0,0,0,0,\ Willie Randolph,23,R,R,"5' 11""",5.916666667,165,Jul 6 1954,4,134,132,134,134,0,0,0,134,0,0,0,0,0,0,0,1,0,\ Mickey Rivers,29,L,L,"5' 10""",5.833333333,165,Oct 31 1948,9,141,135,141,138,0,0,0,0,0,0,0,138,0,138,0,4,1,\ Dennis Sherrill,22,R,R,"6' 0""",6,165,May 3 1956,1st,2,0,2,1,0,0,0,0,1,0,0,0,0,0,0,0,1,\ Jim Spencer,31,L,L,"6' 2""",6.166666667,195,Jul 30 1946,11,71,38,71,15,0,0,15,0,0,0,0,0,0,0,30,27,0,\ Fred Stanley,30,R,R,"5' 10""",5.833333333,165,Aug 13 1947,10,81,48,81,81,0,0,0,12,4,70,0,0,0,0,0,0,4,\ Gary Thomasson,26,L,L,"6' 1""",6.083333333,180,Jul 29 1951,7,54,33,54,49,0,0,0,0,0,0,24,16,12,49,0,6,4,\ Dick Tidrow,31,R,R,"6' 4""",6.333333333,210,May 14 1947,7,31,25,0,31,31,0,0,0,0,0,0,0,0,0,0,0,0,\ Roy White,34,B,R,"5' 10""",5.833333333,160,Dec 27 1943,14,103,94,103,74,0,0,0,0,0,0,74,1,0,74,23,8,0,\ George Zeber,27,B,R,"5' 11""",5.916666667,170,Aug 29 1950,2,3,1,3,1,0,0,0,1,0,0,0,0,0,0,0,2,0,\ ,Age,B,T,Ht,6.071138211,182.6097561,DoB,Yrs,G,GS,Batting,Defense,P,C,1B,2B,3B,SS,LF,CF,RF,OF,DH,PH,PR,} ,,,,,0.85365852,,,,,,,,,,,,,,,,,,,,, \ No newline at end of file diff --git a/Planforms/FDR001.plan b/Planforms/FDR001.plan new file mode 100755 index 0000000..284283a --- /dev/null +++ b/Planforms/FDR001.plan @@ -0,0 +1 @@ +0 85 0 n00155sc.dat 2.32 82.73 2.27 n00155sc.dat 6.38 73.67 11.33 n00155sc.dat 14.2 52.13 30.6 n00155sc.dat 28.98 20 55 nasasc0714.dat 34.77 15 60 nasasc0714.dat 70 7.5 80 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR002.plan b/Planforms/FDR002.plan new file mode 100755 index 0000000..2ffe56b --- /dev/null +++ b/Planforms/FDR002.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 nasasc0714.dat +34.77 15 55 nasasc0714.dat +80 5 93 nasasc0714.dat diff --git a/Planforms/FDR003.plan b/Planforms/FDR003.plan new file mode 100755 index 0000000..0a413cc --- /dev/null +++ b/Planforms/FDR003.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 n2612.dat +34.77 15 55 n2612.dat +80 5 93 n2612.dat diff --git a/Planforms/FDR004.plan b/Planforms/FDR004.plan new file mode 100755 index 0000000..45e5ce6 --- /dev/null +++ b/Planforms/FDR004.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.36 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 nasasc0714.dat +34.77 15 55 nasasc0714.dat +80 5 93 nasasc0714.dat diff --git a/Planforms/FDR005.plan b/Planforms/FDR005.plan new file mode 100755 index 0000000..3452e7d --- /dev/null +++ b/Planforms/FDR005.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 45 nasasc0714.dat +34.77 15 50 nasasc0714.dat +80 5 89 nasasc0714.dat diff --git a/Planforms/FDR006.plan b/Planforms/FDR006.plan new file mode 100755 index 0000000..66116bf --- /dev/null +++ b/Planforms/FDR006.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 25 55 nasasc0714.dat +34.77 20 60 nasasc0714.dat +80 10 82 nasasc0714.dat diff --git a/Planforms/FDR007.plan b/Planforms/FDR007.plan new file mode 100755 index 0000000..8574b44 --- /dev/null +++ b/Planforms/FDR007.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 55 nasasc0714.dat +34.77 15 60 nasasc0714.dat +80 7.5 92 nasasc0714.dat diff --git a/Planforms/FDR008.plan b/Planforms/FDR008.plan new file mode 100755 index 0000000..ff73b6b --- /dev/null +++ b/Planforms/FDR008.plan @@ -0,0 +1,7 @@ +0 85 0 SAX4A.dat +2.32 82.73 2.36 SAX4A.dat +6.38 73.67 11.79 SAX4A.dat +14.2 52.13 31.82 SAX4A.dat +28.98 20 49.5 nasasc0714.dat +34.77 15 56.16 nasasc0714.dat +80 7.5 83.2 nasasc0714.dat diff --git a/Planforms/FDR009.plan b/Planforms/FDR009.plan new file mode 100755 index 0000000..d5ad37f --- /dev/null +++ b/Planforms/FDR009.plan @@ -0,0 +1 @@ +0 95 0 n00155sc.dat 2.32 92.47 2.53 n00155sc.dat 6.38 82.33 12.67 n00165sc.dat 14.2 58.27 34.2 n00165sc.dat 28.98 22.35 55.88 nasasc0714.dat 34.77 16.76 61.47 nasasc0714.dat 80 5.59 103.94 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR010.dat~ b/Planforms/FDR010.dat~ new file mode 100755 index 0000000..1c3101b --- /dev/null +++ b/Planforms/FDR010.dat~ @@ -0,0 +1 @@ +0 85 0 n00165sc.dat 2.32 82.73 2.27 6.38 73.67 11.33 n00165sc.dat 14.20 52.13 27.6 n00165sc.dat 28.98 20 45 nasasc0718.dat 34.77 15 55 nasasc0714.dat 80 5 94 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR010.plan b/Planforms/FDR010.plan new file mode 100755 index 0000000..ec097e7 --- /dev/null +++ b/Planforms/FDR010.plan @@ -0,0 +1 @@ +0 105 0 n00165sc.dat 6.25 99.17 5.83 n00165sc.dat 12 81.67 21 n00165sc.dat 22.1 46.67 46.67 nasasc0721.dat 33.05 23.33 64.17 nasasc0718.dat 80.01 8.75 109.67 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR010.plan~ b/Planforms/FDR010.plan~ new file mode 100755 index 0000000..1c3101b --- /dev/null +++ b/Planforms/FDR010.plan~ @@ -0,0 +1 @@ +0 85 0 n00165sc.dat 2.32 82.73 2.27 6.38 73.67 11.33 n00165sc.dat 14.20 52.13 27.6 n00165sc.dat 28.98 20 45 nasasc0718.dat 34.77 15 55 nasasc0714.dat 80 5 94 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR011.plan b/Planforms/FDR011.plan new file mode 100755 index 0000000..efffc77 --- /dev/null +++ b/Planforms/FDR011.plan @@ -0,0 +1 @@ +0 90 0 n00155sc.dat 6.25 85 5 n00165sc.dat 12 70 18 n00165sc.dat 22.10 40 40 nasasc0718.dat 33.05 20 55 nasasc0714.dat 80.01 7.5 94 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR012.dat~ b/Planforms/FDR012.dat~ new file mode 100755 index 0000000..22f521f --- /dev/null +++ b/Planforms/FDR012.dat~ @@ -0,0 +1 @@ +0 85 0 CB600165a.dat 2.32 82.73 2.27 CB600165a.dat 6.38 73.67 11.33 CB600175a.dat 14.2 52.13 30.6 CB600175a.dat 28.98 20 45 nasasc0718.dat 34.77 15 50 nasasc0714.dat 80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR012.plan b/Planforms/FDR012.plan new file mode 100755 index 0000000..22f521f --- /dev/null +++ b/Planforms/FDR012.plan @@ -0,0 +1 @@ +0 85 0 CB600165a.dat 2.32 82.73 2.27 CB600165a.dat 6.38 73.67 11.33 CB600175a.dat 14.2 52.13 30.6 CB600175a.dat 28.98 20 45 nasasc0718.dat 34.77 15 50 nasasc0714.dat 80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR012.plan~ b/Planforms/FDR012.plan~ new file mode 100755 index 0000000..22f521f --- /dev/null +++ b/Planforms/FDR012.plan~ @@ -0,0 +1 @@ +0 85 0 CB600165a.dat 2.32 82.73 2.27 CB600165a.dat 6.38 73.67 11.33 CB600175a.dat 14.2 52.13 30.6 CB600175a.dat 28.98 20 45 nasasc0718.dat 34.77 15 50 nasasc0714.dat 80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR012.txt b/Planforms/FDR012.txt new file mode 100755 index 0000000..f89f5fb --- /dev/null +++ b/Planforms/FDR012.txt @@ -0,0 +1,8 @@ +0 85 0 CB600155a.dat +2.32 82.73 2.27 CB600155a.dat +6.38 73.67 11.33 n001850sc.dat +10.29 62.9 20.97 n001850sc.dat +14.2 52.13 30.6 n001850sc.dat +28.98 20 45 nasasc0718.dat +34.77 15 50 nasasc0714.dat +80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR012helpme.plan b/Planforms/FDR012helpme.plan new file mode 100755 index 0000000..22f521f --- /dev/null +++ b/Planforms/FDR012helpme.plan @@ -0,0 +1 @@ +0 85 0 CB600165a.dat 2.32 82.73 2.27 CB600165a.dat 6.38 73.67 11.33 CB600175a.dat 14.2 52.13 30.6 CB600175a.dat 28.98 20 45 nasasc0718.dat 34.77 15 50 nasasc0714.dat 80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR013.plan b/Planforms/FDR013.plan new file mode 100755 index 0000000..ca24639 --- /dev/null +++ b/Planforms/FDR013.plan @@ -0,0 +1 @@ +0 83 0 CB600185b.dat 2.32 81.73 1.27 CB600175b.dat 6.38 73.67 9.33 CB600175a.dat 10.29 62.9 18.97 CB600175a.dat 14.2 52.13 28.6 nasasc0714.dat 28.98 20 43 nasasc0714.dat 34.77 15 48 nasasc0714.dat 80 5 87 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR014.plan b/Planforms/FDR014.plan new file mode 100755 index 0000000..7946aba --- /dev/null +++ b/Planforms/FDR014.plan @@ -0,0 +1 @@ +0 83 0 CB600185b.dat 2.32 81.73 1.27 CB600185b.dat 6.38 73.67 9.33 CB600175a.dat 10.29 62.9 18.97 CB600175a.dat 14.2 52.13 25.6 nasasc0714.dat 28.98 20 48 nasasc0714.dat 34.77 15 53 nasasc0714.dat 80 5 90 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR014b.plan b/Planforms/FDR014b.plan new file mode 100755 index 0000000..68d9c0f --- /dev/null +++ b/Planforms/FDR014b.plan @@ -0,0 +1 @@ +0 78.4 0 CB600185b.dat 2.32 76.8 1.22 CB600185b.dat 6.38 68.8 8.96 CB600175a.dat 10.29 57.6 18.21 CB600175a.dat 14.2 50.05 24.58 nasasc0714.dat 28.98 19.2 46.08 nasasc0714.dat 34.77 14.4 50.88 nasasc0714.dat 80 4.8 86.4 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/FDR014c.plan b/Planforms/FDR014c.plan new file mode 100755 index 0000000..f31fd0a Binary files /dev/null and b/Planforms/FDR014c.plan differ diff --git a/Planforms/FDR015.plan b/Planforms/FDR015.plan new file mode 100755 index 0000000..a63371d --- /dev/null +++ b/Planforms/FDR015.plan @@ -0,0 +1,8 @@ +0 100 0 CB600185b.dat +2.32 98.47 1.53 CB600185b.dat +6.38 88.76 11.24 CB600175a.dat +10.29 75.78 22.86 CB600175a.dat +14.2 62.81 34.46 nasasc0714.dat +28.98 24.1 51.81 nasasc0714.dat +34.77 18.07 57.83 nasasc0714.dat +80 6.02 104.82 nasasc0714.dat diff --git a/Planforms/FDR016.plan b/Planforms/FDR016.plan new file mode 100755 index 0000000..5b26354 --- /dev/null +++ b/Planforms/FDR016.plan @@ -0,0 +1,8 @@ +0 97 0 CB600185d.dat +2.32 95.52 1.48 CB600175b.dat +6.38 86.09 10.9 CB600175b.dat +10.29 73.51 22.17 CB600175b.dat +14.2 60.93 33.42 nasasc0714.dat +28.98 23.37 50.25 nasasc0714.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/FDR017.plan b/Planforms/FDR017.plan new file mode 100755 index 0000000..c237f60 --- /dev/null +++ b/Planforms/FDR017.plan @@ -0,0 +1,6 @@ +0 97 0 CB600185d.dat +6.38 88.09 8.9 CB600175b.dat +16 60.93 33.42 nasasc0714.dat +28.98 23.37 50.25 nasasc0714.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/FDR018.plan b/Planforms/FDR018.plan new file mode 100755 index 0000000..3d041f5 --- /dev/null +++ b/Planforms/FDR018.plan @@ -0,0 +1,6 @@ +0 95.2 2 CB600185d.dat +6.38 88.09 8.9 CB600175a.dat +16 60.93 33.42 CB600165a.dat +28.98 23.37 50.25 nasasc0714.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/FDR019.plan b/Planforms/FDR019.plan new file mode 100755 index 0000000..79c749c --- /dev/null +++ b/Planforms/FDR019.plan @@ -0,0 +1,6 @@ +0 98.2 2 CB600185d.dat +6.38 91.09 8.9 CB600175a.dat +16 63.93 33.42 CB600165a.dat +28.98 23.37 50.25 CB600165a.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/FDR020.plan b/Planforms/FDR020.plan new file mode 100755 index 0000000..73b2197 --- /dev/null +++ b/Planforms/FDR020.plan @@ -0,0 +1,6 @@ +0 98.2 2 CB600185d.dat +6.38 91.09 8.9 CB600175a.dat +17 63.93 33.42 CB600165a.dat +28.98 23.37 50.25 CB600165a.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/FDR020ronaldplus.txt b/Planforms/FDR020ronaldplus.txt new file mode 100755 index 0000000..4e8410a --- /dev/null +++ b/Planforms/FDR020ronaldplus.txt @@ -0,0 +1,14 @@ +FDR020--------------------------------------------------- +Wingspan: 160.000000, AR: 4.929075, Planform Area: 5193.672700, Wetted Area: 10834.744604 + +----------Takeoff-------------------------------- + alfa: 10.689189, Cd0: 0.009040, CL: 0.480000, CD: 0.027072, D: 13123.396794, CM: -0.033693, L/D: 16.720004 + +----------Cruise--------------------------------- + alfa: 1.745533, Cd0: 0.005030, CL: 0.149085, CD: 0.006411, D: 7456.834503, CM: -0.036376, L/D: 23.253835 + +----------Loiter--------------------------------- + alfa: 5.303897, Cd0: 0.005450, CL: 0.280744, CD: 0.010403, D: 4961.487808, CM: -0.035309, L/D: 26.987872 + +----------Landing-------------------------------- + alfa: 8.554054, Cd0: 0.008847, CL: 0.401000, CD: 0.019986, D: 12066.388294, CM: -0.034334, L/D: 20.063723 diff --git a/Planforms/PDR001.plan b/Planforms/PDR001.plan new file mode 100755 index 0000000..d1fe611 --- /dev/null +++ b/Planforms/PDR001.plan @@ -0,0 +1,10 @@ +0 88.4 0 CB50015.dat +2.32 86.04 2.36 CB50015.dat +6.38 76.1 11.79 CB50015.dat +14.2 54.22 31.82 nasasc0718.dat +28.98 29.47 49.5 nasasc0718.dat +31.88 25.13 52.83 nasasc0714.dat +34.77 20.8 56.16 nasasc0714.dat +49.89 15.6 69.68 nasasc0714.dat +57.44 13 76.44 nasasc0714.dat +65 10.4 83.2 nasasc0714.dat diff --git a/Planforms/PDR003.plan b/Planforms/PDR003.plan new file mode 100755 index 0000000..e3c7b6f --- /dev/null +++ b/Planforms/PDR003.plan @@ -0,0 +1,10 @@ +0 88.4 0 CB0015.dat +2.32 86.04 2.36 CB0015.dat +6.38 76.1 11.79 CB0015.dat +14.2 54.22 31.82 n0718.dat +28.98 29.47 49.5 nasasc0714.dat +31.88 25.13 52.83 nasasc0714.dat +34.77 20.8 56.16 nasasc0714.dat +49.89 15.6 69.68 nasasc0714.dat +57.44 13 76.44 nasasc0714.dat +65 10.4 83.2 nasasc0714.dat diff --git a/Planforms/Temp/FDR013.tiff b/Planforms/Temp/FDR013.tiff new file mode 100755 index 0000000..02c3019 Binary files /dev/null and b/Planforms/Temp/FDR013.tiff differ diff --git a/Planforms/Temp/FDR013grim.tiff b/Planforms/Temp/FDR013grim.tiff new file mode 100755 index 0000000..e95fc64 Binary files /dev/null and b/Planforms/Temp/FDR013grim.tiff differ diff --git a/Planforms/Temp/FDR014.tiff b/Planforms/Temp/FDR014.tiff new file mode 100755 index 0000000..371732e Binary files /dev/null and b/Planforms/Temp/FDR014.tiff differ diff --git a/Planforms/Temp/FDR014grim.tiff b/Planforms/Temp/FDR014grim.tiff new file mode 100755 index 0000000..8692a6b Binary files /dev/null and b/Planforms/Temp/FDR014grim.tiff differ diff --git a/Planforms/Temp/FDR015.tiff b/Planforms/Temp/FDR015.tiff new file mode 100755 index 0000000..b370d6e Binary files /dev/null and b/Planforms/Temp/FDR015.tiff differ diff --git a/Planforms/Temp/FDR015grim.tiff b/Planforms/Temp/FDR015grim.tiff new file mode 100755 index 0000000..acfe643 Binary files /dev/null and b/Planforms/Temp/FDR015grim.tiff differ diff --git a/Planforms/Temp/FDR016.tiff b/Planforms/Temp/FDR016.tiff new file mode 100755 index 0000000..bfb44c0 Binary files /dev/null and b/Planforms/Temp/FDR016.tiff differ diff --git a/Planforms/Temp/FDR016grim.tiff b/Planforms/Temp/FDR016grim.tiff new file mode 100755 index 0000000..61fa417 Binary files /dev/null and b/Planforms/Temp/FDR016grim.tiff differ diff --git a/Planforms/Temp/FDR017.tiff b/Planforms/Temp/FDR017.tiff new file mode 100755 index 0000000..ca31573 Binary files /dev/null and b/Planforms/Temp/FDR017.tiff differ diff --git a/Planforms/Temp/FDR017grim.tiff b/Planforms/Temp/FDR017grim.tiff new file mode 100755 index 0000000..ca31573 Binary files /dev/null and b/Planforms/Temp/FDR017grim.tiff differ diff --git a/Planforms/Temp/FDR018.tiff b/Planforms/Temp/FDR018.tiff new file mode 100755 index 0000000..5e01f88 Binary files /dev/null and b/Planforms/Temp/FDR018.tiff differ diff --git a/Planforms/Temp/FDR018grim.tiff b/Planforms/Temp/FDR018grim.tiff new file mode 100755 index 0000000..e850618 Binary files /dev/null and b/Planforms/Temp/FDR018grim.tiff differ diff --git a/Planforms/Temp/FDR019.tiff b/Planforms/Temp/FDR019.tiff new file mode 100755 index 0000000..65a768c Binary files /dev/null and b/Planforms/Temp/FDR019.tiff differ diff --git a/Planforms/Temp/FDR019grim.tiff b/Planforms/Temp/FDR019grim.tiff new file mode 100755 index 0000000..294a46e Binary files /dev/null and b/Planforms/Temp/FDR019grim.tiff differ diff --git a/Planforms/Temp/FDR020.tiff b/Planforms/Temp/FDR020.tiff new file mode 100755 index 0000000..729950d Binary files /dev/null and b/Planforms/Temp/FDR020.tiff differ diff --git a/Planforms/Temp/FDR020grim.tiff b/Planforms/Temp/FDR020grim.tiff new file mode 100755 index 0000000..9dd022a Binary files /dev/null and b/Planforms/Temp/FDR020grim.tiff differ diff --git a/Planforms/Temp/FDR020ronaldplus.tiff b/Planforms/Temp/FDR020ronaldplus.tiff new file mode 100755 index 0000000..d8a2530 Binary files /dev/null and b/Planforms/Temp/FDR020ronaldplus.tiff differ diff --git a/Planforms/old daters/FDR001.dat b/Planforms/old daters/FDR001.dat new file mode 100755 index 0000000..f48d941 --- /dev/null +++ b/Planforms/old daters/FDR001.dat @@ -0,0 +1,7 @@ +0 85 0 n0012.dat +2.32 82.73 2.27 n0012.dat +6.38 73.67 11.33 n0012.dat +14.2 52.13 30.6 n0012.dat +28.98 20 55 nasasc0714.dat +34.77 15 60 nasasc0714.dat +70 7.5 80 nasasc0714.dat diff --git a/Planforms/old daters/FDR002.dat b/Planforms/old daters/FDR002.dat new file mode 100755 index 0000000..2ffe56b --- /dev/null +++ b/Planforms/old daters/FDR002.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 nasasc0714.dat +34.77 15 55 nasasc0714.dat +80 5 93 nasasc0714.dat diff --git a/Planforms/old daters/FDR003.dat b/Planforms/old daters/FDR003.dat new file mode 100755 index 0000000..0a413cc --- /dev/null +++ b/Planforms/old daters/FDR003.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 n2612.dat +34.77 15 55 n2612.dat +80 5 93 n2612.dat diff --git a/Planforms/old daters/FDR004.dat b/Planforms/old daters/FDR004.dat new file mode 100755 index 0000000..45e5ce6 --- /dev/null +++ b/Planforms/old daters/FDR004.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.36 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 nasasc0714.dat +34.77 15 55 nasasc0714.dat +80 5 93 nasasc0714.dat diff --git a/Planforms/old daters/FDR005.dat b/Planforms/old daters/FDR005.dat new file mode 100755 index 0000000..3452e7d --- /dev/null +++ b/Planforms/old daters/FDR005.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 45 nasasc0714.dat +34.77 15 50 nasasc0714.dat +80 5 89 nasasc0714.dat diff --git a/Planforms/old daters/FDR006.dat b/Planforms/old daters/FDR006.dat new file mode 100755 index 0000000..66116bf --- /dev/null +++ b/Planforms/old daters/FDR006.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 25 55 nasasc0714.dat +34.77 20 60 nasasc0714.dat +80 10 82 nasasc0714.dat diff --git a/Planforms/old daters/FDR007.dat b/Planforms/old daters/FDR007.dat new file mode 100755 index 0000000..8574b44 --- /dev/null +++ b/Planforms/old daters/FDR007.dat @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 55 nasasc0714.dat +34.77 15 60 nasasc0714.dat +80 7.5 92 nasasc0714.dat diff --git a/Planforms/old daters/FDR008.dat b/Planforms/old daters/FDR008.dat new file mode 100755 index 0000000..ff73b6b --- /dev/null +++ b/Planforms/old daters/FDR008.dat @@ -0,0 +1,7 @@ +0 85 0 SAX4A.dat +2.32 82.73 2.36 SAX4A.dat +6.38 73.67 11.79 SAX4A.dat +14.2 52.13 31.82 SAX4A.dat +28.98 20 49.5 nasasc0714.dat +34.77 15 56.16 nasasc0714.dat +80 7.5 83.2 nasasc0714.dat diff --git a/Planforms/old daters/FDR009.dat b/Planforms/old daters/FDR009.dat new file mode 100755 index 0000000..d5ad37f --- /dev/null +++ b/Planforms/old daters/FDR009.dat @@ -0,0 +1 @@ +0 95 0 n00155sc.dat 2.32 92.47 2.53 n00155sc.dat 6.38 82.33 12.67 n00165sc.dat 14.2 58.27 34.2 n00165sc.dat 28.98 22.35 55.88 nasasc0714.dat 34.77 16.76 61.47 nasasc0714.dat 80 5.59 103.94 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR010.dat b/Planforms/old daters/FDR010.dat new file mode 100755 index 0000000..ec097e7 --- /dev/null +++ b/Planforms/old daters/FDR010.dat @@ -0,0 +1 @@ +0 105 0 n00165sc.dat 6.25 99.17 5.83 n00165sc.dat 12 81.67 21 n00165sc.dat 22.1 46.67 46.67 nasasc0721.dat 33.05 23.33 64.17 nasasc0718.dat 80.01 8.75 109.67 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR011.dat b/Planforms/old daters/FDR011.dat new file mode 100755 index 0000000..efffc77 --- /dev/null +++ b/Planforms/old daters/FDR011.dat @@ -0,0 +1 @@ +0 90 0 n00155sc.dat 6.25 85 5 n00165sc.dat 12 70 18 n00165sc.dat 22.10 40 40 nasasc0718.dat 33.05 20 55 nasasc0714.dat 80.01 7.5 94 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR012.dat b/Planforms/old daters/FDR012.dat new file mode 100755 index 0000000..22f521f --- /dev/null +++ b/Planforms/old daters/FDR012.dat @@ -0,0 +1 @@ +0 85 0 CB600165a.dat 2.32 82.73 2.27 CB600165a.dat 6.38 73.67 11.33 CB600175a.dat 14.2 52.13 30.6 CB600175a.dat 28.98 20 45 nasasc0718.dat 34.77 15 50 nasasc0714.dat 80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR012helpme.dat b/Planforms/old daters/FDR012helpme.dat new file mode 100755 index 0000000..22f521f --- /dev/null +++ b/Planforms/old daters/FDR012helpme.dat @@ -0,0 +1 @@ +0 85 0 CB600165a.dat 2.32 82.73 2.27 CB600165a.dat 6.38 73.67 11.33 CB600175a.dat 14.2 52.13 30.6 CB600175a.dat 28.98 20 45 nasasc0718.dat 34.77 15 50 nasasc0714.dat 80 5 89 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR013.dat b/Planforms/old daters/FDR013.dat new file mode 100755 index 0000000..ca24639 --- /dev/null +++ b/Planforms/old daters/FDR013.dat @@ -0,0 +1 @@ +0 83 0 CB600185b.dat 2.32 81.73 1.27 CB600175b.dat 6.38 73.67 9.33 CB600175a.dat 10.29 62.9 18.97 CB600175a.dat 14.2 52.13 28.6 nasasc0714.dat 28.98 20 43 nasasc0714.dat 34.77 15 48 nasasc0714.dat 80 5 87 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR014.dat b/Planforms/old daters/FDR014.dat new file mode 100755 index 0000000..7946aba --- /dev/null +++ b/Planforms/old daters/FDR014.dat @@ -0,0 +1 @@ +0 83 0 CB600185b.dat 2.32 81.73 1.27 CB600185b.dat 6.38 73.67 9.33 CB600175a.dat 10.29 62.9 18.97 CB600175a.dat 14.2 52.13 25.6 nasasc0714.dat 28.98 20 48 nasasc0714.dat 34.77 15 53 nasasc0714.dat 80 5 90 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR014b.dat b/Planforms/old daters/FDR014b.dat new file mode 100755 index 0000000..68d9c0f --- /dev/null +++ b/Planforms/old daters/FDR014b.dat @@ -0,0 +1 @@ +0 78.4 0 CB600185b.dat 2.32 76.8 1.22 CB600185b.dat 6.38 68.8 8.96 CB600175a.dat 10.29 57.6 18.21 CB600175a.dat 14.2 50.05 24.58 nasasc0714.dat 28.98 19.2 46.08 nasasc0714.dat 34.77 14.4 50.88 nasasc0714.dat 80 4.8 86.4 nasasc0714.dat \ No newline at end of file diff --git a/Planforms/old daters/FDR014c.dat b/Planforms/old daters/FDR014c.dat new file mode 100755 index 0000000..f31fd0a Binary files /dev/null and b/Planforms/old daters/FDR014c.dat differ diff --git a/Planforms/old daters/FDR015.dat b/Planforms/old daters/FDR015.dat new file mode 100755 index 0000000..a63371d --- /dev/null +++ b/Planforms/old daters/FDR015.dat @@ -0,0 +1,8 @@ +0 100 0 CB600185b.dat +2.32 98.47 1.53 CB600185b.dat +6.38 88.76 11.24 CB600175a.dat +10.29 75.78 22.86 CB600175a.dat +14.2 62.81 34.46 nasasc0714.dat +28.98 24.1 51.81 nasasc0714.dat +34.77 18.07 57.83 nasasc0714.dat +80 6.02 104.82 nasasc0714.dat diff --git a/Planforms/old daters/FDR016.dat b/Planforms/old daters/FDR016.dat new file mode 100755 index 0000000..5b26354 --- /dev/null +++ b/Planforms/old daters/FDR016.dat @@ -0,0 +1,8 @@ +0 97 0 CB600185d.dat +2.32 95.52 1.48 CB600175b.dat +6.38 86.09 10.9 CB600175b.dat +10.29 73.51 22.17 CB600175b.dat +14.2 60.93 33.42 nasasc0714.dat +28.98 23.37 50.25 nasasc0714.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/old daters/FDR017.dat b/Planforms/old daters/FDR017.dat new file mode 100755 index 0000000..c237f60 --- /dev/null +++ b/Planforms/old daters/FDR017.dat @@ -0,0 +1,6 @@ +0 97 0 CB600185d.dat +6.38 88.09 8.9 CB600175b.dat +16 60.93 33.42 nasasc0714.dat +28.98 23.37 50.25 nasasc0714.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/old daters/FDR018.dat b/Planforms/old daters/FDR018.dat new file mode 100755 index 0000000..3d041f5 --- /dev/null +++ b/Planforms/old daters/FDR018.dat @@ -0,0 +1,6 @@ +0 95.2 2 CB600185d.dat +6.38 88.09 8.9 CB600175a.dat +16 60.93 33.42 CB600165a.dat +28.98 23.37 50.25 nasasc0714.dat +34.77 17.53 56.1 nasasc0714.dat +80 5.84 101.67 nasasc0714.dat diff --git a/Planforms/old daters/FDR019.dat b/Planforms/old daters/FDR019.dat new file mode 100755 index 0000000..950e174 --- /dev/null +++ b/Planforms/old daters/FDR019.dat @@ -0,0 +1,14 @@ +FDR019.dat--------------------------------------------------- +Wingspan: 160.000000, AR: 4.994194, Planform Area: 5125.952700, Wetted Area: 10692.077365 + +----------Takeoff-------------------------------- + alfa: 11.940482, Cd0: 0.005599, CL: 0.526298, CD: 0.028288, CM: -0.033318, L/D: 18.604902 + +----------Cruise--------------------------------- + alfa: 1.483274, Cd0: 0.004540, CL: 0.139381, CD: 0.006064, CM: -0.036455, L/D: 22.986726 + +----------Loiter--------------------------------- + alfa: 5.180220, Cd0: 0.005250, CL: 0.276168, CD: 0.010265, CM: -0.035346, L/D: 26.902803 + +----------Landing-------------------------------- + alfa: 9.273432, Cd0: 0.005599, CL: 0.427617, CD: 0.018857, CM: -0.034118, L/D: 22.677292 diff --git a/Planforms/old daters/FDR020.dat b/Planforms/old daters/FDR020.dat new file mode 100755 index 0000000..9dbcd4f --- /dev/null +++ b/Planforms/old daters/FDR020.dat @@ -0,0 +1,14 @@ +FDR020.dat--------------------------------------------------- +Wingspan: 160.000000, AR: 4.929075, Planform Area: 5193.672700, Wetted Area: 10834.744604 + +----------Takeoff-------------------------------- + alfa: 11.755013, Cd0: 0.005586, CL: 0.519435, CD: 0.027979, CM: -0.033373, L/D: 18.565355 + +----------Cruise--------------------------------- + alfa: 1.434155, Cd0: 0.004531, CL: 0.137564, CD: 0.006034, CM: -0.036470, L/D: 22.797360 + +----------Loiter--------------------------------- + alfa: 5.082897, Cd0: 0.005238, CL: 0.272567, CD: 0.010188, CM: -0.035375, L/D: 26.754104 + +----------Landing-------------------------------- + alfa: 9.122738, Cd0: 0.005586, CL: 0.422041, CD: 0.018670, CM: -0.034163, L/D: 22.605056 diff --git a/Planforms/old daters/PDR001.dat b/Planforms/old daters/PDR001.dat new file mode 100755 index 0000000..d1fe611 --- /dev/null +++ b/Planforms/old daters/PDR001.dat @@ -0,0 +1,10 @@ +0 88.4 0 CB50015.dat +2.32 86.04 2.36 CB50015.dat +6.38 76.1 11.79 CB50015.dat +14.2 54.22 31.82 nasasc0718.dat +28.98 29.47 49.5 nasasc0718.dat +31.88 25.13 52.83 nasasc0714.dat +34.77 20.8 56.16 nasasc0714.dat +49.89 15.6 69.68 nasasc0714.dat +57.44 13 76.44 nasasc0714.dat +65 10.4 83.2 nasasc0714.dat diff --git a/Planforms/old daters/PDR003.dat b/Planforms/old daters/PDR003.dat new file mode 100755 index 0000000..e3c7b6f --- /dev/null +++ b/Planforms/old daters/PDR003.dat @@ -0,0 +1,10 @@ +0 88.4 0 CB0015.dat +2.32 86.04 2.36 CB0015.dat +6.38 76.1 11.79 CB0015.dat +14.2 54.22 31.82 n0718.dat +28.98 29.47 49.5 nasasc0714.dat +31.88 25.13 52.83 nasasc0714.dat +34.77 20.8 56.16 nasasc0714.dat +49.89 15.6 69.68 nasasc0714.dat +57.44 13 76.44 nasasc0714.dat +65 10.4 83.2 nasasc0714.dat diff --git a/Planforms/old daters/olddater.dat b/Planforms/old daters/olddater.dat new file mode 100755 index 0000000..67bdead --- /dev/null +++ b/Planforms/old daters/olddater.dat @@ -0,0 +1,7 @@ +0, 0.607142857, 0, 'CB50015.dat' +0.016571429, 0.590928571, 0.02, 'CB50015.dat' +0.045571429, 0.526214286, 0.08, 'CB50015.dat' +0.101428571, 0.371428571, 0.22, 'CB50015.dat' +0.207, 0.142857143, 0.39, 'nasasc0718.dat' +0.248357143, 0.107142857, 0.43, 'nasasc0714.dat' +0.5, 0.053571429, 0.54, 'nasasc0714.dat' diff --git a/Planforms/olddater.plan b/Planforms/olddater.plan new file mode 100755 index 0000000..67bdead --- /dev/null +++ b/Planforms/olddater.plan @@ -0,0 +1,7 @@ +0, 0.607142857, 0, 'CB50015.dat' +0.016571429, 0.590928571, 0.02, 'CB50015.dat' +0.045571429, 0.526214286, 0.08, 'CB50015.dat' +0.101428571, 0.371428571, 0.22, 'CB50015.dat' +0.207, 0.142857143, 0.39, 'nasasc0718.dat' +0.248357143, 0.107142857, 0.43, 'nasasc0714.dat' +0.5, 0.053571429, 0.54, 'nasasc0714.dat' diff --git a/Planforms/pranform.bmp b/Planforms/pranform.bmp new file mode 100755 index 0000000..ad572a2 Binary files /dev/null and b/Planforms/pranform.bmp differ diff --git a/Planforms/pranformhalf.bmp b/Planforms/pranformhalf.bmp new file mode 100755 index 0000000..3a81c44 Binary files /dev/null and b/Planforms/pranformhalf.bmp differ diff --git a/Ronald Outputs/Cruise.tif b/Ronald Outputs/Cruise.tif new file mode 100755 index 0000000..1a2abf4 Binary files /dev/null and b/Ronald Outputs/Cruise.tif differ diff --git a/Ronaldplus Outputs/FDR001.txt b/Ronaldplus Outputs/FDR001.txt new file mode 100755 index 0000000..b6d8771 --- /dev/null +++ b/Ronaldplus Outputs/FDR001.txt @@ -0,0 +1,42 @@ +FDR001 +Outputs-------------------------------------------------- +Wingspan: 140.000000, AR: 4.816577, Planform Area: 4069.280000, Wetted Area: 8408.002654 + +----------Takeoff-------------------------------- + alfa: 6.125000, Cd0: 0.009957, CL: 0.480000, CD: 0.028410, D: 10790.513767, CM: -0.582875, L/D: 15.932485 + +----------Cruise--------------------------------- + alfa: 0.951405, Cd0: 0.005179, CL: 0.190279, CD: 0.007481, D: 6817.381579, CM: -0.256939, L/D: 25.434985 + D_Wing:993.322998, D_fuselage:3770.664809 +----------Loiter--------------------------------- + alfa: 3.952095, Cd0: 0.005682, CL: 0.358317, CD: 0.013937, D: 5208.157173, CM: -0.445982, L/D: 25.709670 + +----------Landing-------------------------------- + alfa: 4.714286, Cd0: 0.009735, CL: 0.401000, CD: 0.021135, D: 9997.294077, CM: -0.494000, L/D: 18.973583 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.056 +cLalpha 0.056 cL0 0.137 +cL0 0.137 cMalpha-0.063 +cMalpha-0.063 cM0-0.197 +cM0-0.197 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR002.txt b/Ronaldplus Outputs/FDR002.txt new file mode 100755 index 0000000..ee5094b --- /dev/null +++ b/Ronaldplus Outputs/FDR002.txt @@ -0,0 +1,42 @@ +FDR002 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 5.894737, Cd0: 0.009897, CL: 0.480000, CD: 0.024414, D: 9527.785965, CM: -0.600053, L/D: 18.540333 + +----------Cruise--------------------------------- + alfa: 0.722547, Cd0: 0.005203, CL: 0.185185, CD: 0.006919, D: 6478.628035, CM: -0.258688, L/D: 26.764926 + D_Wing:1155.571422, D_fuselage:3770.664809 +----------Loiter--------------------------------- + alfa: 3.591678, Cd0: 0.005699, CL: 0.348726, CD: 0.011851, D: 4550.243775, CM: -0.448051, L/D: 29.426995 + +----------Landing-------------------------------- + alfa: 4.508772, Cd0: 0.009677, CL: 0.401000, CD: 0.018645, D: 9062.166794, CM: -0.508579, L/D: 21.507190 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.057 +cLalpha 0.057 cL0 0.144 +cL0 0.144 cMalpha-0.066 +cMalpha-0.066 cM0-0.211 +cM0-0.211 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR003.txt b/Ronaldplus Outputs/FDR003.txt new file mode 100755 index 0000000..e3e075e --- /dev/null +++ b/Ronaldplus Outputs/FDR003.txt @@ -0,0 +1,42 @@ +FDR003 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8646.272379 + +----------Takeoff-------------------------------- + alfa: 5.894737, Cd0: 0.009903, CL: 0.480000, CD: 0.024420, D: 9530.278297, CM: -0.600053, L/D: 18.535485 + +----------Cruise--------------------------------- + alfa: 0.722547, Cd0: 0.005208, CL: 0.185185, CD: 0.006924, D: 6483.328324, CM: -0.258688, L/D: 26.745522 + D_Wing:1159.593905, D_fuselage:3771.626725 +----------Loiter--------------------------------- + alfa: 3.591678, Cd0: 0.005704, CL: 0.348726, CD: 0.011856, D: 4552.237898, CM: -0.448051, L/D: 29.414104 + +----------Landing-------------------------------- + alfa: 4.508772, Cd0: 0.009684, CL: 0.401000, CD: 0.018651, D: 9065.211714, CM: -0.508579, L/D: 21.499965 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.057 +cLalpha 0.057 cL0 0.144 +cL0 0.144 cMalpha-0.066 +cMalpha-0.066 cM0-0.211 +cM0-0.211 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR004.txt b/Ronaldplus Outputs/FDR004.txt new file mode 100755 index 0000000..422195d --- /dev/null +++ b/Ronaldplus Outputs/FDR004.txt @@ -0,0 +1,42 @@ +FDR004 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 6.035714, Cd0: 0.009897, CL: 0.480000, CD: 0.024414, D: 9527.785965, CM: -0.601321, L/D: 18.540333 + +----------Cruise--------------------------------- + alfa: 0.771164, Cd0: 0.005203, CL: 0.185185, CD: 0.006919, D: 6478.628035, CM: -0.259126, L/D: 26.764926 + D_Wing:1155.571422, D_fuselage:3770.664809 +----------Loiter--------------------------------- + alfa: 3.691530, Cd0: 0.005699, CL: 0.348726, CD: 0.011851, D: 4550.243775, CM: -0.448949, L/D: 29.426995 + +----------Landing-------------------------------- + alfa: 4.625000, Cd0: 0.009677, CL: 0.401000, CD: 0.018645, D: 9062.166794, CM: -0.509625, L/D: 21.507190 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.056 +cLalpha 0.056 cL0 0.142 +cL0 0.142 cMalpha-0.065 +cMalpha-0.065 cM0-0.209 +cM0-0.209 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR005.txt b/Ronaldplus Outputs/FDR005.txt new file mode 100755 index 0000000..a139a1a --- /dev/null +++ b/Ronaldplus Outputs/FDR005.txt @@ -0,0 +1,42 @@ +FDR005 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 6.035714, Cd0: 0.009897, CL: 0.480000, CD: 0.024414, D: 9527.785965, CM: -0.570214, L/D: 18.540333 + +----------Cruise--------------------------------- + alfa: 0.771164, Cd0: 0.005203, CL: 0.185185, CD: 0.006919, D: 6478.628035, CM: -0.243812, L/D: 26.764926 + D_Wing:1155.571422, D_fuselage:3770.664809 +----------Loiter--------------------------------- + alfa: 3.691530, Cd0: 0.005699, CL: 0.348726, CD: 0.011851, D: 4550.243775, CM: -0.424875, L/D: 29.426995 + +----------Landing-------------------------------- + alfa: 4.625000, Cd0: 0.009677, CL: 0.401000, CD: 0.018645, D: 9062.166794, CM: -0.482750, L/D: 21.507190 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.056 +cLalpha 0.056 cL0 0.142 +cL0 0.142 cMalpha-0.062 +cMalpha-0.062 cM0-0.196 +cM0-0.196 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR006.txt b/Ronaldplus Outputs/FDR006.txt new file mode 100755 index 0000000..888d5cb --- /dev/null +++ b/Ronaldplus Outputs/FDR006.txt @@ -0,0 +1,42 @@ +FDR006 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 5.372164, Planform Area: 4765.305000, Wetted Area: 9841.204819 + +----------Takeoff-------------------------------- + alfa: 5.789474, Cd0: 0.009366, CL: 0.480000, CD: 0.025911, D: 11524.531436, CM: -0.623684, L/D: 17.469300 + +----------Cruise--------------------------------- + alfa: 0.219059, Cd0: 0.005093, CL: 0.162486, CD: 0.006598, D: 7041.632125, CM: -0.244896, L/D: 24.624973 + D_Wing:1611.158629, D_fuselage:3912.112692 +----------Loiter--------------------------------- + alfa: 2.736511, Cd0: 0.005543, CL: 0.305981, CD: 0.010941, D: 4787.724124, CM: -0.416083, L/D: 27.967359 + +----------Landing-------------------------------- + alfa: 4.403509, Cd0: 0.009162, CL: 0.401000, CD: 0.019382, D: 10736.626548, CM: -0.529439, L/D: 20.688886 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.057 +cLalpha 0.057 cL0 0.15 +cL0 0.15 cMalpha-0.068 +cMalpha-0.068 cM0 -0.23 +cM0 -0.23 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR007.txt b/Ronaldplus Outputs/FDR007.txt new file mode 100755 index 0000000..12cf8ac --- /dev/null +++ b/Ronaldplus Outputs/FDR007.txt @@ -0,0 +1,42 @@ +FDR007 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 5.961418, Planform Area: 4294.280000, Wetted Area: 8871.044819 + +----------Takeoff-------------------------------- + alfa: 5.689655, Cd0: 0.009789, CL: 0.480000, CD: 0.024698, D: 9899.382825, CM: -0.646655, L/D: 18.326955 + +----------Cruise--------------------------------- + alfa: 0.522568, Cd0: 0.005184, CL: 0.180309, CD: 0.006854, D: 6591.510141, CM: -0.274625, L/D: 26.306567 + D_Wing:1275.276731, D_fuselage:3770.664809 +----------Loiter--------------------------------- + alfa: 3.267986, Cd0: 0.005670, CL: 0.339543, CD: 0.011659, D: 4597.941876, CM: -0.472295, L/D: 29.121725 + +----------Landing-------------------------------- + alfa: 4.327586, Cd0: 0.009572, CL: 0.401000, CD: 0.018782, D: 9375.811144, CM: -0.548586, L/D: 21.349896 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.058 +cLalpha 0.058 cL0 0.15 +cL0 0.15 cMalpha-0.072 +cMalpha-0.072 cM0-0.237 +cM0-0.237 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR008.txt b/Ronaldplus Outputs/FDR008.txt new file mode 100755 index 0000000..dbac69d --- /dev/null +++ b/Ronaldplus Outputs/FDR008.txt @@ -0,0 +1,42 @@ +FDR008 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 5.961418, Planform Area: 4294.280000, Wetted Area: 8680.251229 + +----------Takeoff-------------------------------- + alfa: 5.689655, Cd0: 0.009659, CL: 0.480000, CD: 0.024568, D: 9847.386405, CM: -0.646655, L/D: 18.423725 + +----------Cruise--------------------------------- + alfa: 0.522568, Cd0: 0.005081, CL: 0.180309, CD: 0.006751, D: 6492.653630, CM: -0.274625, L/D: 26.707108 + D_Wing:1275.276731, D_fuselage:3665.832878 +----------Loiter--------------------------------- + alfa: 3.267986, Cd0: 0.005564, CL: 0.339543, CD: 0.011554, D: 4556.282608, CM: -0.472295, L/D: 29.387993 + +----------Landing-------------------------------- + alfa: 4.327586, Cd0: 0.009445, CL: 0.401000, CD: 0.018655, D: 9312.077689, CM: -0.548586, L/D: 21.496018 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.058 +cLalpha 0.058 cL0 0.15 +cL0 0.15 cMalpha-0.072 +cMalpha-0.072 cM0-0.237 +cM0-0.237 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR009.txt b/Ronaldplus Outputs/FDR009.txt new file mode 100755 index 0000000..22c8b74 --- /dev/null +++ b/Ronaldplus Outputs/FDR009.txt @@ -0,0 +1,42 @@ +FDR009 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 5.478266, Planform Area: 4673.011400, Wetted Area: 9672.757115 + +----------Takeoff-------------------------------- + alfa: 6.490566, Cd0: 0.009421, CL: 0.480000, CD: 0.025645, D: 11185.579599, CM: -0.603415, L/D: 17.650069 + +----------Cruise--------------------------------- + alfa: 0.560293, Cd0: 0.005099, CL: 0.165696, CD: 0.006634, D: 6942.134663, CM: -0.235738, L/D: 24.977908 + D_Wing:1264.133474, D_fuselage:4153.626223 +----------Loiter--------------------------------- + alfa: 3.321215, Cd0: 0.005554, CL: 0.312024, CD: 0.011058, D: 4745.180987, CM: -0.406915, L/D: 28.218102 + +----------Landing-------------------------------- + alfa: 5.000000, Cd0: 0.009216, CL: 0.401000, CD: 0.019238, D: 10450.457803, CM: -0.511000, L/D: 20.843746 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.053 +cLalpha 0.053 cL0 0.136 +cL0 0.136 cMalpha-0.062 +cMalpha-0.062 cM0-0.201 +cM0-0.201 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR010.txt b/Ronaldplus Outputs/FDR010.txt new file mode 100755 index 0000000..22ac2d7 --- /dev/null +++ b/Ronaldplus Outputs/FDR010.txt @@ -0,0 +1,42 @@ +FDR010 +Outputs-------------------------------------------------- +Wingspan: 160.020000, AR: 4.351054, Planform Area: 5885.103300, Wetted Area: 12255.124748 + +----------Takeoff-------------------------------- + alfa: 5.961538, Cd0: 0.008588, CL: 0.480000, CD: 0.029016, D: 15938.254235, CM: -0.569846, L/D: 15.599885 + +----------Cruise--------------------------------- + alfa: -0.739058, Cd0: 0.004911, CL: 0.131569, CD: 0.006130, D: 8078.320210, CM: -0.194613, L/D: 21.464858 + D_Wing:1785.236663, D_fuselage:4837.811550 +----------Loiter--------------------------------- + alfa: 1.495386, Cd0: 0.005295, CL: 0.247760, CD: 0.009664, D: 5222.865680, CM: -0.319742, L/D: 25.637267 + +----------Landing-------------------------------- + alfa: 4.442308, Cd0: 0.008409, CL: 0.401000, CD: 0.021028, D: 14385.111589, CM: -0.484769, L/D: 19.070194 + +Inputs-------------------------------------------------- +laminarflow_to 0.4 laminarflow_cruise 0.4 +laminarflow_cruise 0.4 laminarflow_loiter 0.4 +laminarflow_loiter 0.4 laminarflow_landing 0.4 +laminarflow_landing 0.4 M_cruise 0.8 +M_cruise 0.8 M_to 0.2 +M_to 0.2 M_loiter 0.3 +M_loiter 0.3 M_landing 0.2 +M_landing 0.2 cLalpha 0.052 +cLalpha 0.052 cL0 0.17 +cL0 0.17 cMalpha-0.056 +cMalpha-0.056 cM0-0.236 +cM0-0.236 efficiency_to 0.8 +efficiency_to 0.8 efficiency_cruise 0.8 +efficiency_cruise 0.8 efficiency_loiter 0.8 +efficiency_loiter 0.8 efficiency_landing 0.8 +efficiency_landing 0.8 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise160000 +weight_cruise160000 weight_to160000 +weight_to160000 weight_loiter130000 +weight_loiter130000 weight_landing130000 +weight_landing130000 cd_correction 0 +cd_correction 0 c_f 0.003 diff --git a/Ronaldplus Outputs/FDR020.txt b/Ronaldplus Outputs/FDR020.txt new file mode 100755 index 0000000..f406888 --- /dev/null +++ b/Ronaldplus Outputs/FDR020.txt @@ -0,0 +1,47 @@ +FDR020 +Outputs-------------------------------------------------- +Wingspan: 160.000000, AR: 4.929075, Planform Area: 5193.672700, Wetted Area: 10834.744604 + +----------Takeoff-------------------------------- + alfa: 10.689189, Cd0: 0.009040, CL: 0.480000, CD: 0.027072, D: 13123.396794, CM: -0.033693, L/D: 16.720004 + +----------Cruise--------------------------------- + alfa: 1.745533, Cd0: 0.005030, CL: 0.149085, CD: 0.006411, D: 7456.834503, CM: -0.036376, L/D: 23.253835 + D_Wing:1310.651767, D_fuselage:4652.919001 +----------Loiter--------------------------------- + alfa: 5.303897, Cd0: 0.005450, CL: 0.280744, CD: 0.010403, D: 4961.487808, CM: -0.035309, L/D: 26.987872 + +----------Landing-------------------------------- + alfa: 8.554054, Cd0: 0.008847, CL: 0.401000, CD: 0.019986, D: 12066.388294, CM: -0.034334, L/D: 20.063723 + +Inputs-------------------------------------------------- +laminarflow_to 0.35 laminarflow_cruise 0.5 +laminarflow_cruise 0.5 laminarflow_loiter 0.5 +laminarflow_loiter 0.5 laminarflow_landing 0.35 +laminarflow_landing 0.35 M_cruise 0.8 +M_cruise 0.8 M_to 0.2509 +M_to 0.2509 M_loiter 0.3 +M_loiter 0.3 M_landing 0.28 +M_landing 0.28 cLalpha 0.037 +cLalpha 0.037 cL0 0.0845 +cL0 0.0845 cMalpha 0.0003 +cMalpha 0.0003 cM0-0.0369 +cM0-0.0369 efficiency_to 0.7781 +efficiency_to 0.7781 efficiency_cruise 0.98 +efficiency_cruise 0.98 efficiency_loiter 0.9692 +efficiency_loiter 0.9692 efficiency_landing 0.8791 +efficiency_landing 0.8791 alt_cruise 35000 +alt_cruise 35000 alt_to 0 +alt_to 0 alt_loiter 10000 +alt_loiter 10000 alt_landing 0 +alt_landing 0 weight_cruise 173400 +weight_cruise 173400 weight_to 173400 +weight_to 173400 weight_loiter 133900 +weight_loiter 133900 weight_landing 133900 +weight_landing 133900 cd_correction 0 +cd_correction 0 c_f 0.003 +c_f 0.003 D_engine 240.5 +D_engine 240.5 fuse_width 57.96 +fuse_width 57.96 Dragredux_BLI 5.7 +Dragredux_BLI 5.7 sfront_landinggear 33.7 +sfront_landinggear 33.7 cd_landinggear 0.4 diff --git a/XFLR Outputs/FDR001.out b/XFLR Outputs/FDR001.out new file mode 100755 index 0000000..f7bcfb6 --- /dev/null +++ b/XFLR Outputs/FDR001.out @@ -0,0 +1,53 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR001 +Wing polar name : kickin' ass +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.006842 0.000251 0.000000 0.000251 0.000000 -0.026050 0.000000 -0.000000 -0.000000 9.7536 0.4046 + -0.900 0.011881 0.000243 0.000000 0.000243 -0.000000 -0.032028 0.000000 0.000000 0.000000 9.7536 0.2865 + -0.800 0.017486 0.000242 0.000000 0.000242 0.000000 -0.038399 -0.000000 -0.000000 -0.000000 9.7536 0.2333 + -0.700 0.023090 0.000245 0.000000 0.000245 0.000000 -0.044770 0.000000 -0.000000 -0.000000 9.7536 0.2060 + -0.600 0.028695 0.000252 0.000000 0.000252 0.000000 -0.051140 0.000000 -0.000000 -0.000000 9.7536 0.1894 + -0.500 0.034863 0.000267 0.000000 0.000267 -0.000000 -0.057902 0.000000 0.000000 0.000000 9.7536 0.1765 + -0.400 0.039903 0.000279 0.000000 0.000279 0.000000 -0.063881 0.000000 -0.000000 -0.000000 9.7536 0.1701 + -0.300 0.045507 0.000300 0.000000 0.000300 -0.000000 -0.070251 -0.000000 0.000000 0.000000 9.7536 0.1640 + -0.200 0.051111 0.000325 0.000000 0.000325 0.000000 -0.076621 0.000000 0.000000 0.000000 9.7536 0.1593 + -0.100 0.056714 0.000354 0.000000 0.000354 -0.000000 -0.082991 0.000000 -0.000000 -0.000000 9.7536 0.1555 + 0.000 0.062882 0.000392 0.000000 0.000392 0.000000 -0.089751 0.000000 -0.000000 -0.000000 9.7536 0.1516 + 0.100 0.067920 0.000425 0.000000 0.000425 0.000000 -0.095729 0.000000 0.000000 0.000000 9.7536 0.1497 + 0.200 0.073522 0.000467 0.000000 0.000467 -0.000000 -0.102097 -0.000000 -0.000000 -0.000000 9.7536 0.1475 + 0.300 0.079124 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9.7536 0.1293 + + diff --git a/XFLR Outputs/FDR004.out b/XFLR Outputs/FDR004.out new file mode 100755 index 0000000..18bada4 --- /dev/null +++ b/XFLR Outputs/FDR004.out @@ -0,0 +1,20 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR004 +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.085107 0.000981 0.000000 0.000981 0.000000 -0.142817 0.000000 -0.000000 -0.000000 9.7536 0.1523 + -0.500 0.113515 0.001143 0.000000 0.001143 -0.000000 -0.175844 -0.000000 0.000000 0.000000 9.7536 0.1406 + 0.000 0.141908 0.001402 0.000000 0.001402 -0.000000 -0.208848 0.000000 0.000000 0.000000 9.7536 0.1336 + 0.500 0.170279 0.001759 0.000000 0.001759 -0.000000 -0.241821 0.000000 0.000000 0.000000 9.7536 0.1289 + 1.000 0.198620 0.002213 0.000000 0.002213 0.000000 -0.274753 0.000000 0.000000 0.000000 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_________ _________ _________ _________ _________ _________ _________ + -1.000 0.091190 0.001207 0.000000 0.001207 -0.000000 -0.163135 -0.000000 0.000000 0.000000 9.7536 0.1534 + -0.500 0.120608 0.001405 0.000000 0.001405 0.000000 -0.199971 -0.000000 0.000000 0.000000 9.7536 0.1421 + 0.000 0.150010 0.001701 0.000000 0.001701 -0.000000 -0.236781 -0.000000 0.000000 0.000000 9.7536 0.1353 + 0.500 0.179388 0.002095 0.000000 0.002095 0.000000 -0.273556 0.000000 -0.000000 -0.000000 9.7536 0.1307 + 1.000 0.208736 0.002586 0.000000 0.002586 0.000000 -0.310284 -0.000000 -0.000000 -0.000000 9.7536 0.1274 + 1.500 0.238045 0.003175 0.000000 0.003175 0.000000 -0.346954 0.000000 0.000000 0.000000 9.7536 0.1250 + 2.000 0.267309 0.003860 0.000000 0.003860 -0.000000 -0.383554 -0.000000 -0.000000 -0.000000 9.7536 0.1230 + 2.500 0.296520 0.004642 0.000000 0.004642 0.000000 -0.420074 0.000000 0.000000 0.000000 9.7536 0.1215 + 3.000 0.325671 0.005520 0.000000 0.005520 0.000000 -0.456501 0.000000 0.000000 0.000000 9.7536 0.1203 + + diff --git a/XFLR Outputs/FDR007.txt b/XFLR Outputs/FDR007.txt new file mode 100755 index 0000000..a4427b0 --- /dev/null +++ b/XFLR Outputs/FDR007.txt @@ -0,0 +1,20 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR007 +Wing polar name : kickin' ass -inviscid +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.091190 0.001207 0.000000 0.001207 -0.000000 -0.163135 -0.000000 0.000000 0.000000 9.7536 0.1534 + -0.500 0.120608 0.001405 0.000000 0.001405 0.000000 -0.199971 -0.000000 0.000000 0.000000 9.7536 0.1421 + 0.000 0.150010 0.001701 0.000000 0.001701 -0.000000 -0.236781 -0.000000 0.000000 0.000000 9.7536 0.1353 + 0.500 0.179388 0.002095 0.000000 0.002095 0.000000 -0.273556 0.000000 -0.000000 -0.000000 9.7536 0.1307 + 1.000 0.208736 0.002586 0.000000 0.002586 0.000000 -0.310284 -0.000000 -0.000000 -0.000000 9.7536 0.1274 + 1.500 0.238045 0.003175 0.000000 0.003175 0.000000 -0.346954 0.000000 0.000000 0.000000 9.7536 0.1250 + 2.000 0.267309 0.003860 0.000000 0.003860 -0.000000 -0.383554 -0.000000 -0.000000 -0.000000 9.7536 0.1230 + 2.500 0.296520 0.004642 0.000000 0.004642 0.000000 -0.420074 0.000000 0.000000 0.000000 9.7536 0.1215 + 3.000 0.325671 0.005520 0.000000 0.005520 0.000000 -0.456501 0.000000 0.000000 0.000000 9.7536 0.1203 + + diff --git a/XFLR Outputs/FDR008.out b/XFLR Outputs/FDR008.out new file mode 100755 index 0000000..f0a18b0 --- /dev/null +++ b/XFLR Outputs/FDR008.out @@ -0,0 +1,20 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR008 +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.102761 0.001092 0.000000 0.001092 0.000000 -0.171934 -0.000000 -0.000000 -0.000000 9.7536 0.1434 + -0.500 0.132184 0.001345 0.000000 0.001345 0.000000 -0.208771 -0.000000 -0.000000 -0.000000 9.7536 0.1354 + 0.000 0.161587 0.001696 0.000000 0.001696 0.000000 -0.245585 0.000000 -0.000000 -0.000000 9.7536 0.1303 + 0.500 0.190964 0.002145 0.000000 0.002145 0.000000 -0.282364 0.000000 -0.000000 -0.000000 9.7536 0.1267 + 1.000 0.220308 0.002692 0.000000 0.002692 -0.000000 -0.319097 0.000000 0.000000 0.000000 9.7536 0.1241 + 1.500 0.249610 0.003335 0.000000 0.003335 -0.000000 -0.355774 -0.000000 0.000000 0.000000 9.7536 0.1222 + 2.000 0.278864 0.004075 0.000000 0.004075 -0.000000 -0.392382 -0.000000 0.000000 0.000000 9.7536 0.1207 + 2.500 0.308063 0.004912 0.000000 0.004912 -0.000000 -0.428911 0.000000 0.000000 0.000000 9.7536 0.1194 + 3.000 0.337198 0.005845 0.000000 0.005845 0.000000 -0.465350 0.000000 -0.000000 -0.000000 9.7536 0.1184 + + diff --git a/XFLR Outputs/FDR008.txt b/XFLR Outputs/FDR008.txt new file mode 100755 index 0000000..f0a18b0 --- /dev/null +++ b/XFLR Outputs/FDR008.txt @@ -0,0 +1,20 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR008 +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.102761 0.001092 0.000000 0.001092 0.000000 -0.171934 -0.000000 -0.000000 -0.000000 9.7536 0.1434 + -0.500 0.132184 0.001345 0.000000 0.001345 0.000000 -0.208771 -0.000000 -0.000000 -0.000000 9.7536 0.1354 + 0.000 0.161587 0.001696 0.000000 0.001696 0.000000 -0.245585 0.000000 -0.000000 -0.000000 9.7536 0.1303 + 0.500 0.190964 0.002145 0.000000 0.002145 0.000000 -0.282364 0.000000 -0.000000 -0.000000 9.7536 0.1267 + 1.000 0.220308 0.002692 0.000000 0.002692 -0.000000 -0.319097 0.000000 0.000000 0.000000 9.7536 0.1241 + 1.500 0.249610 0.003335 0.000000 0.003335 -0.000000 -0.355774 -0.000000 0.000000 0.000000 9.7536 0.1222 + 2.000 0.278864 0.004075 0.000000 0.004075 -0.000000 -0.392382 -0.000000 0.000000 0.000000 9.7536 0.1207 + 2.500 0.308063 0.004912 0.000000 0.004912 -0.000000 -0.428911 0.000000 0.000000 0.000000 9.7536 0.1194 + 3.000 0.337198 0.005845 0.000000 0.005845 0.000000 -0.465350 0.000000 -0.000000 -0.000000 9.7536 0.1184 + + diff --git a/XFLR Outputs/FDR009.out b/XFLR Outputs/FDR009.out new file mode 100755 index 0000000..e5498be --- /dev/null +++ b/XFLR Outputs/FDR009.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sF DR009 Wing polar name : T1 -32.0 ft/s 0 0ft Freestream speed : 3 2.000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ -2 0.028775 0.000902 0.039073 0.039975 0 -0.075392 0 0 0 9.7536 0.266 -1.5 0.055659 0.000888 0.039687 0.040574 0 -0.106895 0 0 0 9.7536 0.1949 -1 0.082543 0.00097 0.039993 0.040963 0 -0.138397 0 0 0 9.7536 0.1701 -0.5 0.109418 0.001148 0.045594 0.046742 0 -0.169891 0 0 0 9.7536 0.1575 0 0.136278 0.001422 0.049288 0.05071 0 -0.201364 0 0 0 9.7536 0.1499 0.5 0.163116 0.001792 0.051593 0.053384 0 -0.232805 0 0 0 9.7536 0.1448 1 0.189924 0.002257 0.054106 0.056363 0 -0.264205 0 0 0 9.7536 0.1412 1.5 0.216697 0.002817 0.057404 0.060221 0 -0.295557 0 0 0 9.7536 0.1384 2 0.243426 0.003472 0.05946 0.062932 0 -0.326849 0 0 0 9.7536 0.1363 2.5 0.270105 0.004222 0.062187 0.066409 0 -0.358073 0 0 0 9.7536 0.1346 3 0.296727 0.005065 0.064045 0.06911 0 -0.389217 0 0 0 9.7536 0.1333 3.5 0.323284 0.006002 0.066155 0.072157 0 -0.420274 0 0 0 9.7536 0.1321 4 0.34977 0.007031 0.070139 0.07717 0 -0.451235 0 0 0 9.7536 0.1312 \ No newline at end of file diff --git a/XFLR Outputs/FDR009.txt b/XFLR Outputs/FDR009.txt new file mode 100755 index 0000000..a14a45f --- /dev/null +++ b/XFLR Outputs/FDR009.txt @@ -0,0 +1,21 @@ +QFLR5 v0.04 Beta + +Wing name : sF DR009 +Wing polar name : T1 -32.0 ft/s 0 0ft +Freestream speed : 3 2.000 ft/s + +alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP +_________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ +-2 0.028775 0.000902 0.039073 0.039975 0 -0.075392 0 0 0 9.7536 0.266 +-1.5 0.055659 0.000888 0.039687 0.040574 0 -0.106895 0 0 0 9.7536 0.1949 +-1 0.082543 0.00097 0.039993 0.040963 0 -0.138397 0 0 0 9.7536 0.1701 +-0.5 0.109418 0.001148 0.045594 0.046742 0 -0.169891 0 0 0 9.7536 0.1575 +0 0.136278 0.001422 0.049288 0.05071 0 -0.201364 0 0 0 9.7536 0.1499 +0.5 0.163116 0.001792 0.051593 0.053384 0 -0.232805 0 0 0 9.7536 0.1448 +1 0.189924 0.002257 0.054106 0.056363 0 -0.264205 0 0 0 9.7536 0.1412 +1.5 0.216697 0.002817 0.057404 0.060221 0 -0.295557 0 0 0 9.7536 0.1384 +2 0.243426 0.003472 0.05946 0.062932 0 -0.326849 0 0 0 9.7536 0.1363 +2.5 0.270105 0.004222 0.062187 0.066409 0 -0.358073 0 0 0 9.7536 0.1346 +3 0.296727 0.005065 0.064045 0.06911 0 -0.389217 0 0 0 9.7536 0.1333 +3.5 0.323284 0.006002 0.066155 0.072157 0 -0.420274 0 0 0 9.7536 0.1321 +4 0.34977 0.007031 0.070139 0.07717 0 -0.451235 0 0 0 9.7536 0.1312 \ No newline at end of file diff --git a/XFLR Outputs/FDR010.out b/XFLR Outputs/FDR010.out new file mode 100755 index 0000000..d8800b8 --- /dev/null +++ b/XFLR Outputs/FDR010.out @@ -0,0 +1,24 @@ + + QFLR5 v0.04 Beta + +Wing name : FDR010s +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.116962 0.001621 0.051031 0.052652 -0.000000 -0.178726 -0.000000 0.000000 -0.000000 9.7536 0.1726 + -0.500 0.143347 0.002042 0.056144 0.058186 0.000000 -0.207479 0.000000 0.000000 0.000000 9.7536 0.1635 + 0.000 0.169707 0.002565 0.058118 0.060682 -0.000000 -0.236203 -0.000000 0.000000 0.000000 9.7536 0.1572 + 0.500 0.196033 0.003189 0.059796 0.062985 -0.000000 -0.264890 0.000000 0.000000 0.000000 9.7536 0.1526 + 1.000 0.222318 0.003914 0.063433 0.067347 -0.000000 -0.293535 -0.000000 0.000000 0.000000 9.7536 0.1491 + 1.500 0.248556 0.004739 0.064884 0.069623 -0.000000 -0.322125 0.000000 0.000000 0.000000 9.7536 0.1464 + 2.000 0.274738 0.005665 0.066241 0.071906 0.000000 -0.350652 -0.000000 0.000000 -0.000000 9.7536 0.1442 + 2.500 0.300858 0.006689 0.067503 0.074192 0.000000 -0.379109 -0.000000 0.000000 0.000000 9.7536 0.1424 + 3.000 0.326908 0.007813 0.068834 0.076647 0.000000 -0.407487 -0.000000 0.000000 0.000000 9.7536 0.1410 + 3.500 0.352881 0.009034 0.070760 0.079794 0.000000 -0.435777 -0.000000 0.000000 -0.000000 9.7536 0.1397 + 4.000 0.378770 0.010353 0.075051 0.085405 0.000000 -0.463973 0.000000 0.000000 0.000000 9.7536 0.1387 + 4.500 0.404568 0.011768 0.082388 0.094156 -0.000000 -0.492068 -0.000000 0.000000 0.000000 9.7536 0.1378 + 5.000 0.430268 0.013279 0.082849 0.096128 0.000000 -0.520042 0.000000 0.000000 0.000000 9.7536 0.1370 + + diff --git a/XFLR Outputs/FDR010.txt b/XFLR Outputs/FDR010.txt new file mode 100755 index 0000000..d8800b8 --- /dev/null +++ b/XFLR Outputs/FDR010.txt @@ -0,0 +1,24 @@ + + QFLR5 v0.04 Beta + +Wing name : FDR010s +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.116962 0.001621 0.051031 0.052652 -0.000000 -0.178726 -0.000000 0.000000 -0.000000 9.7536 0.1726 + -0.500 0.143347 0.002042 0.056144 0.058186 0.000000 -0.207479 0.000000 0.000000 0.000000 9.7536 0.1635 + 0.000 0.169707 0.002565 0.058118 0.060682 -0.000000 -0.236203 -0.000000 0.000000 0.000000 9.7536 0.1572 + 0.500 0.196033 0.003189 0.059796 0.062985 -0.000000 -0.264890 0.000000 0.000000 0.000000 9.7536 0.1526 + 1.000 0.222318 0.003914 0.063433 0.067347 -0.000000 -0.293535 -0.000000 0.000000 0.000000 9.7536 0.1491 + 1.500 0.248556 0.004739 0.064884 0.069623 -0.000000 -0.322125 0.000000 0.000000 0.000000 9.7536 0.1464 + 2.000 0.274738 0.005665 0.066241 0.071906 0.000000 -0.350652 -0.000000 0.000000 -0.000000 9.7536 0.1442 + 2.500 0.300858 0.006689 0.067503 0.074192 0.000000 -0.379109 -0.000000 0.000000 0.000000 9.7536 0.1424 + 3.000 0.326908 0.007813 0.068834 0.076647 0.000000 -0.407487 -0.000000 0.000000 0.000000 9.7536 0.1410 + 3.500 0.352881 0.009034 0.070760 0.079794 0.000000 -0.435777 -0.000000 0.000000 -0.000000 9.7536 0.1397 + 4.000 0.378770 0.010353 0.075051 0.085405 0.000000 -0.463973 0.000000 0.000000 0.000000 9.7536 0.1387 + 4.500 0.404568 0.011768 0.082388 0.094156 -0.000000 -0.492068 -0.000000 0.000000 0.000000 9.7536 0.1378 + 5.000 0.430268 0.013279 0.082849 0.096128 0.000000 -0.520042 0.000000 0.000000 0.000000 9.7536 0.1370 + + diff --git a/XFLR Outputs/FDR012.txt b/XFLR Outputs/FDR012.txt new file mode 100755 index 0000000..6cfdae2 --- /dev/null +++ b/XFLR Outputs/FDR012.txt @@ -0,0 +1,17 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR012 +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + 0.000 0.144128 0.001339 0.000000 0.001339 0.000000 -0.198932 -0.000000 -0.000000 -0.000000 9.7536 0.1202 + 1.000 0.202051 0.002148 0.000000 0.002148 0.000000 -0.262090 0.000000 0.000000 0.000000 9.7536 0.1130 + 2.000 0.259825 0.003355 0.000000 0.003355 0.000000 -0.325051 -0.000000 -0.000000 -0.000000 9.7536 0.1091 + 3.000 0.317389 0.004957 0.000000 0.004957 -0.000000 -0.387737 -0.000000 -0.000000 -0.000000 9.7536 0.1066 + 4.000 0.374686 0.006950 0.000000 0.006950 0.000000 -0.450073 0.000000 0.000000 0.000000 9.7536 0.1049 + 5.000 0.431657 0.009328 0.000000 0.009328 0.000000 -0.511982 -0.000000 -0.000000 -0.000000 9.7536 0.1037 + + diff --git a/XFLR Outputs/FDR013.out b/XFLR Outputs/FDR013.out new file mode 100755 index 0000000..54d7359 --- /dev/null +++ b/XFLR Outputs/FDR013.out @@ -0,0 +1,14 @@ +QFLR5 v0.04 Beta + +Wing name : sF DR013 +Wing polar name : T1 -105.0 ft/ s-VLM2- 0. 00ft-Invisc id +Freestream speed : 10 4.990 ft/s + +alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP +_________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ +0 0.197841 0.002619 0 0.002619 0 -0.267136 0 0 0 32.001 0.1217 +1 0.254737 0.00402 0 0.00402 0 -0.327464 0 0 0 32.001 0.1159 +2 0.311422 0.005817 0 0.005817 0 -0.387557 0 0 0 32.001 0.1123 +3 0.367837 0.008003 0 0.008003 0 -0.447341 0 0 0 32.001 0.1098 +4 0.423924 0.010575 0 0.010575 0 -0.506744 0 0 0 32.001 0.108 +5 0.479626 0.013523 0 0.013523 0 -0.565693 0 0 0 32.001 0.1067 diff --git a/XFLR Outputs/FDR013.txt b/XFLR Outputs/FDR013.txt new file mode 100755 index 0000000..0bf1412 --- /dev/null +++ b/XFLR Outputs/FDR013.txt @@ -0,0 +1,17 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR013 +Wing polar name : T1-32.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + 0.000 0.197841 0.002619 0.000000 0.002619 0.000000 -0.267136 -0.000000 -0.000000 -0.000000 9.7536 0.1217 + 1.000 0.254737 0.004020 0.000000 0.004020 -0.000000 -0.327464 -0.000000 -0.000000 -0.000000 9.7536 0.1159 + 2.000 0.311422 0.005817 0.000000 0.005817 0.000000 -0.387557 -0.000000 0.000000 0.000000 9.7536 0.1123 + 3.000 0.367837 0.008003 0.000000 0.008003 0.000000 -0.447341 0.000000 -0.000000 -0.000000 9.7536 0.1098 + 4.000 0.423924 0.010575 0.000000 0.010575 -0.000000 -0.506744 -0.000000 -0.000000 -0.000000 9.7536 0.1080 + 5.000 0.479626 0.013523 0.000000 0.013523 -0.000000 -0.565693 0.000000 -0.000000 -0.000000 9.7536 0.1067 + + diff --git a/XFLR Outputs/FDR020.out b/XFLR Outputs/FDR020.out new file mode 100755 index 0000000..5dc4375 --- /dev/null +++ b/XFLR Outputs/FDR020.out @@ -0,0 +1,15 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR020 +Wing polar name : T1-32.0 ft/s-Panel- 0.31ft +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + 0.000 0.084447 0.000837 0.042292 0.043129 -0.000000 -0.036884 0.000000 -0.000000 -0.000000 9.7536 0.1450 + 1.000 0.121470 0.001267 0.048979 0.050246 0.000000 -0.036566 0.000000 -0.000000 -0.000000 9.7536 0.1286 + 2.000 0.158434 0.001864 0.053171 0.055035 -0.000000 -0.036226 0.000000 -0.000000 0.000000 9.7536 0.1198 + 3.000 0.195321 0.002624 0.058185 0.060809 -0.000000 -0.035866 0.000000 -0.000000 0.000000 9.7536 0.1144 + + diff --git a/XFLR Outputs/FDR020.txt b/XFLR Outputs/FDR020.txt new file mode 100755 index 0000000..5dc4375 --- /dev/null +++ b/XFLR Outputs/FDR020.txt @@ -0,0 +1,15 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR020 +Wing polar name : T1-32.0 ft/s-Panel- 0.31ft +Freestream speed : 32.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + 0.000 0.084447 0.000837 0.042292 0.043129 -0.000000 -0.036884 0.000000 -0.000000 -0.000000 9.7536 0.1450 + 1.000 0.121470 0.001267 0.048979 0.050246 0.000000 -0.036566 0.000000 -0.000000 -0.000000 9.7536 0.1286 + 2.000 0.158434 0.001864 0.053171 0.055035 -0.000000 -0.036226 0.000000 -0.000000 0.000000 9.7536 0.1198 + 3.000 0.195321 0.002624 0.058185 0.060809 -0.000000 -0.035866 0.000000 -0.000000 0.000000 9.7536 0.1144 + + diff --git a/XFLR Outputs/PDR001.out b/XFLR Outputs/PDR001.out new file mode 100755 index 0000000..31e4d15 --- /dev/null +++ b/XFLR Outputs/PDR001.out @@ -0,0 +1,15 @@ + + QFLR5 v0.04 Beta + +Wing name : whole damn thing scaled +Wing polar name : T1-16.0 ft/s-VLM2- 0.00ft +Freestream speed : 16.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -0.500 0.141086 0.003049 0.059669 0.062717 0.000000 -0.216817 -0.000000 -0.000000 0.000000 4.8768 0.1839 + 0.000 0.167846 0.003683 0.068042 0.071725 -0.000000 -0.245851 0.000000 -0.000000 -0.000000 4.8768 0.1752 + 0.500 0.194566 0.004440 0.071442 0.075882 -0.000000 -0.274840 0.000000 -0.000000 -0.000000 4.8768 0.1690 + 1.000 0.221238 0.005319 0.074465 0.079784 -0.000000 -0.303781 0.000000 -0.000000 -0.000000 4.8768 0.1643 + + diff --git a/XFLR Outputs/PDR001.txt b/XFLR Outputs/PDR001.txt new file mode 100755 index 0000000..31e4d15 --- /dev/null +++ b/XFLR Outputs/PDR001.txt @@ -0,0 +1,15 @@ + + QFLR5 v0.04 Beta + +Wing name : whole damn thing scaled +Wing polar name : T1-16.0 ft/s-VLM2- 0.00ft +Freestream speed : 16.000 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -0.500 0.141086 0.003049 0.059669 0.062717 0.000000 -0.216817 -0.000000 -0.000000 0.000000 4.8768 0.1839 + 0.000 0.167846 0.003683 0.068042 0.071725 -0.000000 -0.245851 0.000000 -0.000000 -0.000000 4.8768 0.1752 + 0.500 0.194566 0.004440 0.071442 0.075882 -0.000000 -0.274840 0.000000 -0.000000 -0.000000 4.8768 0.1690 + 1.000 0.221238 0.005319 0.074465 0.079784 -0.000000 -0.303781 0.000000 -0.000000 -0.000000 4.8768 0.1643 + + diff --git a/XFLR Outputs/T1-105.0 ft s-VLM2- 0.out b/XFLR Outputs/T1-105.0 ft s-VLM2- 0.out new file mode 100755 index 0000000..9ba8280 --- /dev/null +++ b/XFLR Outputs/T1-105.0 ft s-VLM2- 0.out @@ -0,0 +1,18 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR012 +Wing polar name : T1-105.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 104.990 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.086115 0.000931 0.000000 0.000931 0.000000 -0.135653 -0.000000 0.000000 0.000000 32.0010 0.1373 + 0.000 0.144128 0.001339 0.000000 0.001339 -0.000000 -0.198932 0.000000 0.000000 0.000000 32.0010 0.1202 + 1.000 0.202051 0.002148 0.000000 0.002148 -0.000000 -0.262090 -0.000000 -0.000000 -0.000000 32.0010 0.1130 + 2.000 0.259825 0.003355 0.000000 0.003355 -0.000000 -0.325051 0.000000 -0.000000 -0.000000 32.0010 0.1091 + 3.000 0.317390 0.004957 0.000000 0.004957 -0.000000 -0.387737 -0.000000 0.000000 0.000000 32.0010 0.1066 + 4.000 0.374686 0.006950 0.000000 0.006950 -0.000000 -0.450073 -0.000000 0.000000 0.000000 32.0010 0.1049 + 5.000 0.431657 0.009328 0.000000 0.009328 -0.000000 -0.511982 0.000000 -0.000000 -0.000000 32.0010 0.1037 + + diff --git a/XFLR Outputs/T1-105.0 ft s-VLM2- 0.txt b/XFLR Outputs/T1-105.0 ft s-VLM2- 0.txt new file mode 100755 index 0000000..9ba8280 --- /dev/null +++ b/XFLR Outputs/T1-105.0 ft s-VLM2- 0.txt @@ -0,0 +1,18 @@ + + QFLR5 v0.04 Beta + +Wing name : sFDR012 +Wing polar name : T1-105.0 ft/s-VLM2- 0.00ft-Inviscid +Freestream speed : 104.990 ft/s + + alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP + _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ + -1.000 0.086115 0.000931 0.000000 0.000931 0.000000 -0.135653 -0.000000 0.000000 0.000000 32.0010 0.1373 + 0.000 0.144128 0.001339 0.000000 0.001339 -0.000000 -0.198932 0.000000 0.000000 0.000000 32.0010 0.1202 + 1.000 0.202051 0.002148 0.000000 0.002148 -0.000000 -0.262090 -0.000000 -0.000000 -0.000000 32.0010 0.1130 + 2.000 0.259825 0.003355 0.000000 0.003355 -0.000000 -0.325051 0.000000 -0.000000 -0.000000 32.0010 0.1091 + 3.000 0.317390 0.004957 0.000000 0.004957 -0.000000 -0.387737 -0.000000 0.000000 0.000000 32.0010 0.1066 + 4.000 0.374686 0.006950 0.000000 0.006950 -0.000000 -0.450073 -0.000000 0.000000 0.000000 32.0010 0.1049 + 5.000 0.431657 0.009328 0.000000 0.009328 -0.000000 -0.511982 0.000000 -0.000000 -0.000000 32.0010 0.1037 + + diff --git a/XFLR Outputs/Trade Study planform/.DS_Store b/XFLR Outputs/Trade Study planform/.DS_Store new file mode 100644 index 0000000..7b78527 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/.DS_Store differ diff --git a/XFLR Outputs/Trade Study planform/FDR001.out b/XFLR Outputs/Trade Study planform/FDR001.out new file mode 100755 index 0000000..121f02d --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR001.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R001 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.137049 0.00184 0 0.00184 0 -0.196487 0 0 0 9.7536 0.1493 1 0.193603 0.002851 0 0.002851 0 -0.2607 0 0 0 9.7536 0.1403 2 0.249997 0.004295 0 0.004295 0 -0.324716 0 0 0 9.7536 0.1353 3 0.306168 0.006169 0 0.006169 0 -0.388457 0 0 0 9.7536 0.1323 4 0.362055 0.008467 0 0.008467 0 -0.451845 0 0 0 9.7536 0.1303 5 0.417594 0.011183 0 0.011183 0 -0.514802 0 0 0 9.7536 0.1289 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR001.param b/XFLR Outputs/Trade Study planform/FDR001.param new file mode 100755 index 0000000..f49f0f4 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR001.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.137 cMalpha -.063 cM0 -0.197 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR001.plan b/XFLR Outputs/Trade Study planform/FDR001.plan new file mode 100755 index 0000000..284283a --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR001.plan @@ -0,0 +1 @@ +0 85 0 n00155sc.dat 2.32 82.73 2.27 n00155sc.dat 6.38 73.67 11.33 n00155sc.dat 14.2 52.13 30.6 n00155sc.dat 28.98 20 55 nasasc0714.dat 34.77 15 60 nasasc0714.dat 70 7.5 80 nasasc0714.dat \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR001grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR001grimlite.tiff new file mode 100755 index 0000000..996403e Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR001grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR001grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR001grimliteoutput.txt new file mode 100755 index 0000000..a7ebab4 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR001grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR001--------------------------------------------------- +Wingspan: 140.000000, AR: 4.816577, Planform Area: 4069.280000, Wetted Area: 8408.002654 + +----------Takeoff-------------------------------- + alfa: 9.392178, Cd0: 0.005688, CL: 0.662962, CD: 0.041996, CM: -0.788707, L/D: 15.786333 + +----------Cruise--------------------------------- + alfa: 0.688827, Cd0: 0.004598, CL: 0.175574, CD: 0.007145, CM: -0.240396, L/D: 24.573681 + +----------Loiter--------------------------------- + alfa: 3.765730, Cd0: 0.005328, CL: 0.347881, CD: 0.015325, CM: -0.434241, L/D: 22.699622 + +----------Landing-------------------------------- + alfa: 7.172439, Cd0: 0.005688, CL: 0.538657, CD: 0.029657, CM: -0.648864, L/D: 18.162885 diff --git a/XFLR Outputs/Trade Study planform/FDR002.out b/XFLR Outputs/Trade Study planform/FDR002.out new file mode 100755 index 0000000..5473f97 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR002.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R002 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.143858 0.001392 0 0.001392 0 -0.211427 0 0 0 9.7536 0.128 1 0.201677 0.002192 0 0.002192 0 -0.278415 0 0 0 9.7536 0.1203 2 0.259348 0.003382 0 0.003382 0 -0.345194 0 0 0 9.7536 0.116 3 0.316815 0.004958 0 0.004958 0 -0.411682 0 0 0 9.7536 0.1134 4 0.374019 0.006917 0 0.006917 0 -0.477797 0 0 0 9.7536 0.1116 5 0.430904 0.009252 0 0.009252 0 -0.54346 0 0 0 9.7536 0.1103 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR002.param b/XFLR Outputs/Trade Study planform/FDR002.param new file mode 100755 index 0000000..6a2bbdb --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR002.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.057 cL0 0.144 cMalpha -.066 cM0 -0.211 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR002.plan b/XFLR Outputs/Trade Study planform/FDR002.plan new file mode 100755 index 0000000..c130d9a --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR002.plan @@ -0,0 +1 @@ +0 85 0 n00155sc.dat 2.32 82.73 2.27 n00155sc.dat 6.38 73.67 11.33 n00155sc.dat 14.2 52.13 30.6 n00155sc.dat 28.98 20 50 nasasc0714.dat 34.77 15 55 nasasc0714.dat 80 5 93 nasasc0714.dat \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR002grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR002grimlite.tiff new file mode 100755 index 0000000..fa3b0b7 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR002grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR002grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR002grimliteoutput.txt new file mode 100755 index 0000000..04b219b --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR002grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR002--------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 8.793252, Cd0: 0.005750, CL: 0.645215, CD: 0.032804, CM: -0.791355, L/D: 19.668736 + +----------Cruise--------------------------------- + alfa: 0.471481, Cd0: 0.004640, CL: 0.170874, CD: 0.006538, CM: -0.242118, L/D: 26.135980 + +----------Loiter--------------------------------- + alfa: 3.413484, Cd0: 0.005383, CL: 0.338569, CD: 0.012832, CM: -0.436290, L/D: 26.383862 + +----------Landing-------------------------------- + alfa: 6.670833, Cd0: 0.005750, CL: 0.524237, CD: 0.023610, CM: -0.651275, L/D: 22.204057 diff --git a/XFLR Outputs/Trade Study planform/FDR003.out b/XFLR Outputs/Trade Study planform/FDR003.out new file mode 100755 index 0000000..45e88fb --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR003.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R003 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.143858 0.001392 0 0.001392 0 -0.211427 0 0 0 9.7536 0.128 1 0.201677 0.002192 0 0.002192 0 -0.278415 0 0 0 9.7536 0.1203 2 0.259348 0.003382 0 0.003382 0 -0.345194 0 0 0 9.7536 0.116 3 0.316815 0.004958 0 0.004958 0 -0.411682 0 0 0 9.7536 0.1134 4 0.374019 0.006917 0 0.006917 0 -0.477797 0 0 0 9.7536 0.1116 5 0.430904 0.009252 0 0.009252 0 -0.54346 0 0 0 9.7536 0.1103 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR003.param b/XFLR Outputs/Trade Study planform/FDR003.param new file mode 100755 index 0000000..6a2bbdb --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR003.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.057 cL0 0.144 cMalpha -.066 cM0 -0.211 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR003.plan b/XFLR Outputs/Trade Study planform/FDR003.plan new file mode 100755 index 0000000..c130d9a --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR003.plan @@ -0,0 +1 @@ +0 85 0 n00155sc.dat 2.32 82.73 2.27 n00155sc.dat 6.38 73.67 11.33 n00155sc.dat 14.2 52.13 30.6 n00155sc.dat 28.98 20 50 nasasc0714.dat 34.77 15 55 nasasc0714.dat 80 5 93 nasasc0714.dat \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR003grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR003grimlite.tiff new file mode 100755 index 0000000..40cb343 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR003grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR003grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR003grimliteoutput.txt new file mode 100755 index 0000000..64a957c --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR003grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR003--------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 8.793252, Cd0: 0.005750, CL: 0.645215, CD: 0.032804, CM: -0.791355, L/D: 19.668736 + +----------Cruise--------------------------------- + alfa: 0.471481, Cd0: 0.004640, CL: 0.170874, CD: 0.006538, CM: -0.242118, L/D: 26.135980 + +----------Loiter--------------------------------- + alfa: 3.413484, Cd0: 0.005383, CL: 0.338569, CD: 0.012832, CM: -0.436290, L/D: 26.383862 + +----------Landing-------------------------------- + alfa: 6.670833, Cd0: 0.005750, CL: 0.524237, CD: 0.023610, CM: -0.651275, L/D: 22.204057 diff --git a/XFLR Outputs/Trade Study planform/FDR004.out b/XFLR Outputs/Trade Study planform/FDR004.out new file mode 100755 index 0000000..4bad2e2 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR004.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R004 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.141908 0.001402 0 0.001402 0 -0.208848 0 0 0 9.7536 0.1336 1 0.19862 0.002213 0 0.002213 0 -0.274753 0 0 0 9.7536 0.1255 2 0.255186 0.003411 0 0.003411 0 -0.34045 0 0 0 9.7536 0.1211 3 0.311548 0.004994 0 0.004994 0 -0.40586 0 0 0 9.7536 0.1184 4 0.367649 0.006957 0 0.006957 0 -0.470904 0 0 0 9.7536 0.1165 5 0.423432 0.009295 0 0.009295 0 -0.535502 0 0 0 9.7536 0.1152 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR004.param b/XFLR Outputs/Trade Study planform/FDR004.param new file mode 100755 index 0000000..da46bc2 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR004.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.142 cMalpha -.065 cM0 -0.209 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR004.plan b/XFLR Outputs/Trade Study planform/FDR004.plan new file mode 100755 index 0000000..45e5ce6 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR004.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.36 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 50 nasasc0714.dat +34.77 15 55 nasasc0714.dat +80 5 93 nasasc0714.dat diff --git a/XFLR Outputs/Trade Study planform/FDR004grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR004grimlite.tiff new file mode 100755 index 0000000..9af0c69 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR004grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR004grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR004grimliteoutput.txt new file mode 100755 index 0000000..ccfa63a --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR004grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR004--------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 8.985989, Cd0: 0.005750, CL: 0.645215, CD: 0.032804, CM: -0.793089, L/D: 19.668736 + +----------Cruise--------------------------------- + alfa: 0.515615, Cd0: 0.004640, CL: 0.170874, CD: 0.006538, CM: -0.242515, L/D: 26.135980 + +----------Loiter--------------------------------- + alfa: 3.510154, Cd0: 0.005383, CL: 0.338569, CD: 0.012832, CM: -0.437160, L/D: 26.383862 + +----------Landing-------------------------------- + alfa: 6.825670, Cd0: 0.005750, CL: 0.524237, CD: 0.023610, CM: -0.652669, L/D: 22.204057 diff --git a/XFLR Outputs/Trade Study planform/FDR005.out b/XFLR Outputs/Trade Study planform/FDR005.out new file mode 100755 index 0000000..3b8800f --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR005.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R005 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ -1 0.085162 0.000927 0 0.000927 0 -0.134114 0 0 0 9.7536 0.1429 -0.5 0.113619 0.001087 0 0.001087 0 -0.165237 0 0 0 9.7536 0.132 0 0.142061 0.001347 0 0.001347 0 -0.19634 0 0 0 9.7536 0.1254 0.5 0.17048 0.001707 0 0.001707 0 -0.227413 0 0 0 9.7536 0.1211 0.509 0.171006 0.001714 0 0.001714 0 -0.227987 0 0 0 9.7536 0.121 0.512 0.171157 0.001717 0 0.001717 0 -0.228153 0 0 0 9.7536 0.121 1 0.19887 0.002166 0 0.002166 0 -0.258447 0 0 0 9.7536 0.1179 1.5 0.227222 0.002724 0 0.002724 0 -0.289432 0 0 0 9.7536 0.1156 2 0.255529 0.00338 0 0.00338 0 -0.320359 0 0 0 9.7536 0.1138 2.5 0.283785 0.004135 0 0.004135 0 -0.351218 0 0 0 9.7536 0.1124 3 0.311981 0.004988 0 0.004988 0 -0.382 0 0 0 9.7536 0.1113 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR005.param b/XFLR Outputs/Trade Study planform/FDR005.param new file mode 100755 index 0000000..be37bbc --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR005.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.056 cL0 0.142 cMalpha -.062 cM0 -0.196 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR005.plan b/XFLR Outputs/Trade Study planform/FDR005.plan new file mode 100755 index 0000000..3452e7d --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR005.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 45 nasasc0714.dat +34.77 15 50 nasasc0714.dat +80 5 89 nasasc0714.dat diff --git a/XFLR Outputs/Trade Study planform/FDR005grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR005grimlite.tiff new file mode 100755 index 0000000..5a1627d Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR005grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR005grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR005grimliteoutput.txt new file mode 100755 index 0000000..888268d --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR005grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR005--------------------------------------------------- +Wingspan: 160.000000, AR: 6.122637, Planform Area: 4181.205000, Wetted Area: 8638.340407 + +----------Takeoff-------------------------------- + alfa: 8.985989, Cd0: 0.005750, CL: 0.645215, CD: 0.032804, CM: -0.753131, L/D: 19.668736 + +----------Cruise--------------------------------- + alfa: 0.515615, Cd0: 0.004640, CL: 0.170874, CD: 0.006538, CM: -0.227968, L/D: 26.135980 + +----------Loiter--------------------------------- + alfa: 3.510154, Cd0: 0.005383, CL: 0.338569, CD: 0.012832, CM: -0.413630, L/D: 26.383862 + +----------Landing-------------------------------- + alfa: 6.825670, Cd0: 0.005750, CL: 0.524237, CD: 0.023610, CM: -0.619192, L/D: 22.204057 diff --git a/XFLR Outputs/Trade Study planform/FDR006.out b/XFLR Outputs/Trade Study planform/FDR006.out new file mode 100755 index 0000000..a8be828 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR006.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sF DR006 Wing polar name : T1 -32.0 ft/s 0 0ft-Inviscid Freestream speed : 3 2.000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.149715 0.002561 0 0.002561 0 -0.23 0 0 0 9.7536 0.1563 1 0.207344 0.003856 0 0.003856 0 -0.299477 0 0 0 9.7536 0.147 2 0.264788 0.00562 0 0.00562 0 -0.36873 0 0 0 9.7536 0.1418 3 0.321981 0.00785 0 0.00785 0 -0.437675 0 0 0 9.7536 0.1385 4 0.378857 0.010538 0 0.010538 0 -0.506227 0 0 0 9.7536 0.1363 5 0.43535 0.013679 0 0.013679 0 -0.574303 0 0 0 9.7536 0.1347 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR006.param b/XFLR Outputs/Trade Study planform/FDR006.param new file mode 100755 index 0000000..c19620f --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR006.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.057 cL0 0.150 cMalpha -.068 cM0 -0.230 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR006.plan b/XFLR Outputs/Trade Study planform/FDR006.plan new file mode 100755 index 0000000..66116bf --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR006.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 25 55 nasasc0714.dat +34.77 20 60 nasasc0714.dat +80 10 82 nasasc0714.dat diff --git a/XFLR Outputs/Trade Study planform/FDR006grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR006grimlite.tiff new file mode 100755 index 0000000..ab0116f Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR006grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR006grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR006grimliteoutput.txt new file mode 100755 index 0000000..ae8f060 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR006grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR006--------------------------------------------------- +Wingspan: 160.000000, AR: 5.372164, Planform Area: 4765.305000, Wetted Area: 9841.204819 + +----------Takeoff-------------------------------- + alfa: 7.300510, Cd0: 0.005716, CL: 0.566129, CD: 0.029454, CM: -0.726435, L/D: 19.220819 + +----------Cruise--------------------------------- + alfa: -0.001232, Cd0: 0.004619, CL: 0.149930, CD: 0.006284, CM: -0.229916, L/D: 23.859484 + +----------Loiter--------------------------------- + alfa: 2.580159, Cd0: 0.005354, CL: 0.297069, CD: 0.011890, CM: -0.405451, L/D: 24.985343 + +----------Landing-------------------------------- + alfa: 5.438244, Cd0: 0.005716, CL: 0.459980, CD: 0.021387, CM: -0.599801, L/D: 21.507670 diff --git a/XFLR Outputs/Trade Study planform/FDR007.out b/XFLR Outputs/Trade Study planform/FDR007.out new file mode 100755 index 0000000..c69300e --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR007.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R007 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.15001 0.001701 0 0.001701 0 -0.236781 0 0 0 9.7536 0.1353 1 0.208736 0.002586 0 0.002586 0 -0.310284 0 0 0 9.7536 0.1274 2 0.267309 0.00386 0 0.00386 0 -0.383554 0 0 0 9.7536 0.123 3 0.325671 0.00552 0 0.00552 0 -0.456501 0 0 0 9.7536 0.1203 4 0.383763 0.007561 0 0.007561 0 -0.529037 0 0 0 9.7536 0.1184 5 0.441528 0.009978 0 0.009978 0 -0.601073 0 0 0 9.7536 0.1171 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR007.param b/XFLR Outputs/Trade Study planform/FDR007.param new file mode 100755 index 0000000..d3b3e21 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR007.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.058 cL0 0.150 cMalpha -.072 cM0 -0.237 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR007.plan b/XFLR Outputs/Trade Study planform/FDR007.plan new file mode 100755 index 0000000..8574b44 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR007.plan @@ -0,0 +1,7 @@ +0 85 0 n00155sc.dat +2.32 82.73 2.27 n00155sc.dat +6.38 73.67 11.33 n00155sc.dat +14.2 52.13 30.6 n00155sc.dat +28.98 20 55 nasasc0714.dat +34.77 15 60 nasasc0714.dat +80 7.5 92 nasasc0714.dat diff --git a/XFLR Outputs/Trade Study planform/FDR007grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR007grimlite.tiff new file mode 100755 index 0000000..510fd99 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR007grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR007grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR007grimliteoutput.txt new file mode 100755 index 0000000..b069c4d --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR007grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR007--------------------------------------------------- +Wingspan: 160.000000, AR: 5.961418, Planform Area: 4294.280000, Wetted Area: 8871.044819 + +----------Takeoff-------------------------------- + alfa: 8.245274, Cd0: 0.005754, CL: 0.628226, CD: 0.032095, CM: -0.830660, L/D: 19.573691 + +----------Cruise--------------------------------- + alfa: 0.282329, Cd0: 0.004644, CL: 0.166375, CD: 0.006491, CM: -0.257328, L/D: 25.631038 + +----------Loiter--------------------------------- + alfa: 3.097476, Cd0: 0.005387, CL: 0.329654, CD: 0.012640, CM: -0.460018, L/D: 26.080567 + +----------Landing-------------------------------- + alfa: 6.214371, Cd0: 0.005754, CL: 0.510434, CD: 0.023143, CM: -0.684435, L/D: 22.055258 diff --git a/XFLR Outputs/Trade Study planform/FDR008.out b/XFLR Outputs/Trade Study planform/FDR008.out new file mode 100755 index 0000000..65baa63 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR008.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R008 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.15001 0.001701 0 0.001701 0 -0.236781 0 0 0 9.7536 0.1353 1 0.208736 0.002586 0 0.002586 0 -0.310284 0 0 0 9.7536 0.1274 2 0.267309 0.00386 0 0.00386 0 -0.383554 0 0 0 9.7536 0.123 3 0.325671 0.00552 0 0.00552 0 -0.456501 0 0 0 9.7536 0.1203 4 0.383763 0.007561 0 0.007561 0 -0.529037 0 0 0 9.7536 0.1184 5 0.441528 0.009978 0 0.009978 0 -0.601073 0 0 0 9.7536 0.1171 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR008.param b/XFLR Outputs/Trade Study planform/FDR008.param new file mode 100755 index 0000000..d3b3e21 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR008.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.058 cL0 0.150 cMalpha -.072 cM0 -0.237 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR008.plan b/XFLR Outputs/Trade Study planform/FDR008.plan new file mode 100755 index 0000000..28a70d3 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR008.plan @@ -0,0 +1 @@ +0 85 0 n00155sc.dat 2.32 82.73 2.36 n00155sc.dat 6.38 73.67 11.79 n00155sc.dat 14.2 52.13 31.82 n00155sc.dat 28.98 20 49.5 nasasc0714.dat 34.77 15 56.16 nasasc0714.dat 80 7.5 83.2 nasasc0714.dat \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR008grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR008grimlite.tiff new file mode 100755 index 0000000..f997a25 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR008grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR008grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR008grimliteoutput.txt new file mode 100755 index 0000000..608c881 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR008grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR008--------------------------------------------------- +Wingspan: 160.000000, AR: 5.961418, Planform Area: 4294.280000, Wetted Area: 8871.044819 + +----------Takeoff-------------------------------- + alfa: 8.245274, Cd0: 0.005754, CL: 0.628226, CD: 0.032095, CM: -0.830660, L/D: 19.573691 + +----------Cruise--------------------------------- + alfa: 0.282329, Cd0: 0.004644, CL: 0.166375, CD: 0.006491, CM: -0.257328, L/D: 25.631038 + +----------Loiter--------------------------------- + alfa: 3.097476, Cd0: 0.005387, CL: 0.329654, CD: 0.012640, CM: -0.460018, L/D: 26.080567 + +----------Landing-------------------------------- + alfa: 6.214371, Cd0: 0.005754, CL: 0.510434, CD: 0.023143, CM: -0.684435, L/D: 22.055258 diff --git a/XFLR Outputs/Trade Study planform/FDR009.out b/XFLR Outputs/Trade Study planform/FDR009.out new file mode 100755 index 0000000..2c78f9a --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR009.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFDR 9 Wing polar name : T1-3 2.0 ft/s 0 0ft-Inviscid Freestream speed : 32. 000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.136278 0.001422 0 0.001422 0 -0.20134 0 0 0 9.7536 0.1499 1 0.189924 0.002257 0 0.002257 0 -0.264178 0 0 0 9.7536 0.1412 2 0.243426 0.003472 0 0.003472 0 -0.326817 0 0 0 9.7536 0.1363 3 0.296727 0.005065 0 0.005065 0 -0.389181 0 0 0 9.7536 0.1333 4 0.34977 0.007031 0 0.007031 0 -0.451194 0 0 0 9.7536 0.1312 5 0.402502 0.009365 0 0.009365 0 -0.512781 0 0 0 9.7536 0.1298 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR009.param b/XFLR Outputs/Trade Study planform/FDR009.param new file mode 100755 index 0000000..6a7598f --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR009.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.053 cL0 0.136 cMalpha -.062 cM0 -0.201 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR009.plan b/XFLR Outputs/Trade Study planform/FDR009.plan new file mode 100755 index 0000000..04735ae --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR009.plan @@ -0,0 +1 @@ +0 95 0 n00155sc.dat 2.32 92.47 2.53 n00155sc.dat 6.38 82.33 12.67 n00155sc.dat 14.2 58.27 34.2 n00155sc.dat 28.98 22.35 55.88 nasasc0714.dat 34.77 16.76 61.47 nasasc0714.dat 80 5.59 103.94 nasasc0714.dat \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR009grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR009grimlite.tiff new file mode 100755 index 0000000..00e914b Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR009grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR009grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR009grimliteoutput.txt new file mode 100755 index 0000000..4c70ecd --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR009grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR009--------------------------------------------------- +Wingspan: 160.000000, AR: 5.478266, Planform Area: 4673.011400, Wetted Area: 9654.410650 + +----------Takeoff-------------------------------- + alfa: 8.326610, Cd0: 0.005645, CL: 0.577310, CD: 0.029852, CM: -0.717250, L/D: 19.339016 + +----------Cruise--------------------------------- + alfa: 0.318697, Cd0: 0.004567, CL: 0.152891, CD: 0.006265, CM: -0.220759, L/D: 24.404627 + +----------Loiter--------------------------------- + alfa: 3.149741, Cd0: 0.005289, CL: 0.302936, CD: 0.011955, CM: -0.396284, L/D: 25.340758 + +----------Landing-------------------------------- + alfa: 6.284239, Cd0: 0.005645, CL: 0.469065, CD: 0.021626, CM: -0.590623, L/D: 21.690241 diff --git a/XFLR Outputs/Trade Study planform/FDR010.out b/XFLR Outputs/Trade Study planform/FDR010.out new file mode 100755 index 0000000..e77a296 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR010.out @@ -0,0 +1 @@ +QFLR5 v0.04 Beta Wing name : sFD R010 Wing polar name : T1- 32.0 ft/s 0 0ft-Inviscid Freestream speed : 32 .000 ft/s alpha CL ICd PCd TCd CY Cm Rm Ym IYm QInf XCP _________ ________ ________ _________ _________ _________ _________ _________ _________ _________ _________ _________ 0 0.169653 0.002563 0 0.002563 0 -0.236039 0 0 0 9.7536 0.1572 1 0.222264 0.003912 0 0.003912 0 -0.293367 0 0 0 9.7536 0.1491 2 0.274684 0.005662 0 0.005662 0 -0.350482 0 0 0 9.7536 0.1442 3 0.326854 0.00781 0 0.00781 0 -0.407315 0 0 0 9.7536 0.1409 4 0.378716 0.01035 0 0.01035 0 -0.463796 0 0 0 9.7536 0.1387 5 0.430215 0.013275 0 0.013275 0 -0.519856 0 0 0 9.7536 0.137 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR010.param b/XFLR Outputs/Trade Study planform/FDR010.param new file mode 100755 index 0000000..d727138 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR010.param @@ -0,0 +1 @@ +laminarflow_to .40 laminarflow_cruise .40 laminarflow_loiter .40 laminarflow_landing .40 M_cruise 0.8 M_to 0.2 M_loiter 0.3 M_landing 0.2 cLalpha 0.052 cL0 0.170 cMalpha -.056 cM0 -0.236 efficiency_to 0.8 efficiency_cruise 0.8 efficiency_loiter 0.8 efficiency_landing 0.8 alt_cruise 35000 alt_to 0 alt_loiter 10000 alt_landing 0 weight_cruise 160000 weight_to 160000 weight_loiter 130000 weight_landing 130000 cd_correction 0 c_f 0.003 \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR010.plan b/XFLR Outputs/Trade Study planform/FDR010.plan new file mode 100755 index 0000000..ec097e7 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR010.plan @@ -0,0 +1 @@ +0 105 0 n00165sc.dat 6.25 99.17 5.83 n00165sc.dat 12 81.67 21 n00165sc.dat 22.1 46.67 46.67 nasasc0721.dat 33.05 23.33 64.17 nasasc0718.dat 80.01 8.75 109.67 nasasc0714.dat \ No newline at end of file diff --git a/XFLR Outputs/Trade Study planform/FDR010grimlite.tiff b/XFLR Outputs/Trade Study planform/FDR010grimlite.tiff new file mode 100755 index 0000000..5957fe0 Binary files /dev/null and b/XFLR Outputs/Trade Study planform/FDR010grimlite.tiff differ diff --git a/XFLR Outputs/Trade Study planform/FDR010grimliteoutput.txt b/XFLR Outputs/Trade Study planform/FDR010grimliteoutput.txt new file mode 100755 index 0000000..4f232e7 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/FDR010grimliteoutput.txt @@ -0,0 +1,14 @@ +FDR010--------------------------------------------------- +Wingspan: 160.020000, AR: 4.351054, Planform Area: 5885.103300, Wetted Area: 12255.124748 + +----------Takeoff-------------------------------- + alfa: 5.546306, Cd0: 0.005524, CL: 0.458408, CD: 0.024740, CM: -0.546593, L/D: 18.529145 + +----------Cruise--------------------------------- + alfa: -0.934584, Cd0: 0.004487, CL: 0.121402, CD: 0.005835, CM: -0.183663, L/D: 20.806322 + +----------Loiter--------------------------------- + alfa: 1.356610, Cd0: 0.005182, CL: 0.240544, CD: 0.010473, CM: -0.311970, L/D: 22.967682 + +----------Landing-------------------------------- + alfa: 3.893393, Cd0: 0.005524, CL: 0.372456, CD: 0.018209, CM: -0.454030, L/D: 20.454199 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR001.param b/XFLR Outputs/Trade Study planform/Old Param/FDR001.param new file mode 100755 index 0000000..db92ee9 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR001.param @@ -0,0 +1,15 @@ +M_cruise 0.8 +M_landing 0.2 +cLalpha_cruise 0.0559 +cLalpha_landing 0.053 +cMalpha_cruise -0.0636 +efficiency 1.016 + +alt_cruise 35000 +weight_cruise 160000 + + +cL0 0.0624 +cM0 -0.0894 +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR002.param b/XFLR Outputs/Trade Study planform/Old Param/FDR002.param new file mode 100755 index 0000000..8fc2a3b --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR002.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0571 +cL0 0.1421 +cMalpha_cruise -0.0661 +cM0 -0.2092 + +efficiency 0.8501 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR003.param b/XFLR Outputs/Trade Study planform/Old Param/FDR003.param new file mode 100755 index 0000000..24438c4 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR003.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0572 +cL0 0.0717 +cMalpha_cruise -0.0663 +cM0 -0.106 + +efficiency 1.0089 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR004.param b/XFLR Outputs/Trade Study planform/Old Param/FDR004.param new file mode 100755 index 0000000..1d53bf5 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR004.param @@ -0,0 +1,15 @@ +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0566 +cL0 0.1419 +cMalpha_cruise -0.0658 +cM0 -0.2088 + +efficiency 0.8591 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR005.param b/XFLR Outputs/Trade Study planform/Old Param/FDR005.param new file mode 100755 index 0000000..ad26c95 --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR005.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0567 +cL0 0.142 +cMalpha_cruise -0.062 +cM0 -0.1963 + +efficiency 0.8872 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR006.param b/XFLR Outputs/Trade Study planform/Old Param/FDR006.param new file mode 100755 index 0000000..fa4750c --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR006.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise .0575 +cL0 0.1497 +cMalpha_cruise -0.0693 +cM0 -0.23 + +efficiency 0.652 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR007.param b/XFLR Outputs/Trade Study planform/Old Param/FDR007.param new file mode 100755 index 0000000..afcc5ac --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR007.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0586 +cL0 0.15 +cMalpha_cruise -0.0734 +cM0 -0.2367 + +efficiency 0.7437 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR008.param b/XFLR Outputs/Trade Study planform/Old Param/FDR008.param new file mode 100755 index 0000000..8afa4dc --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR008.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.0586 +cL0 0.1616 +cMalpha_cruise -0.0734 +cM0 -0.2455 + +efficiency 0.8049 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR009.param b/XFLR Outputs/Trade Study planform/Old Param/FDR009.param new file mode 100755 index 0000000..ad6b3bf --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR009.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.053 +cL0 0.136 +cMalpha_cruise -0.062 +cM0 -0.201 + +efficiency 0.9683 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Outputs/Trade Study planform/Old Param/FDR010.param b/XFLR Outputs/Trade Study planform/Old Param/FDR010.param new file mode 100755 index 0000000..076cfae --- /dev/null +++ b/XFLR Outputs/Trade Study planform/Old Param/FDR010.param @@ -0,0 +1,16 @@ +wingspan 160 +M_cruise 0.8 +M_landing 0.2 + +cLalpha_cruise 0.052 +cL0 0.169 +cMalpha_cruise -0.056 +cM0 -0.236 + +efficiency 0.8049 + +alt_cruise 35000 +weight_cruise 160000 + +cd_correction 0 +c_f 0.003 diff --git a/XFLR Project Files/FDR013.wpa b/XFLR Project Files/FDR013.wpa new file mode 100755 index 0000000..5b30cd9 Binary files /dev/null and b/XFLR Project Files/FDR013.wpa differ diff --git a/XFLR Project Files/FDR020.wpa b/XFLR Project Files/FDR020.wpa new file mode 100755 index 0000000..a4d116a Binary files /dev/null and b/XFLR Project Files/FDR020.wpa differ diff --git a/XFLR Project 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