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Anthony Correa
2010-04-17 12:00:00 -05:00
commit 0da2092d89
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Matlab code/Legacy/.DS_Store vendored Normal file
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Matlab code/Legacy/Jacobi/Airfoils/CB30015.dat Executable file
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Centerbody 3
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0.927426 0.031964

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Matlab code/Legacy/Jacobi/Planforms/AirData.dat Executable file
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0 0.610000000000000 0 n0011sc.dat

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Matlab code/Legacy/Jacobi/Planforms/AirData.mat Executable file
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Matlab code/Legacy/Jacobi/Planforms/FDR001.avl Executable file
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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 nasasc2-0714.dat
34.77 15 60 nasasc2-0714.dat
70 7.5 803 nasasc2-0714.dat

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Matlab code/Legacy/Jacobi/Planforms/olddater.dat Executable file
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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, 'nasasc-718.dat'
0.248357143, 0.107142857, 0.43, 'nasasc2-714.dat'
0.5, 0.053571429, 0.54, 'nasasc2-714.dat'

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Matlab code/Legacy/Jacobi/WhettedArea.m Executable file
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%function Area = WhettedArea( fileName, wingSpan )
function WhettedArea(fileName,wingSpan, n)
% fileName = 'AirData.mat';
% wingSpan = 1;
% n = 50;
Area = 0;
pranformArea = 0;
PlanData1 = load(fileName);
PlanData = PlanData1.(fileName(1:end-4));
Chords = findChords(n, PlanData);
for i = 1:(size(PlanData,1)-1)
for j = 1:n
dist = wingSpan*(PlanData{i+1,1}-PlanData{i,1})./n;
Area = Area+findPerim( PlanData{i,4}, Chords(i,j), wingSpan).*dist;
% fprintf('Chord: %f Perimiter: %f Area: %f\n', Chords(i,j), findPerim( PlanData{i,4}, Chords(i,j), wingSpan), Area)
end
end
for i = 1:(size(PlanData,1)-1)
for j = 1:n
dist = wingSpan*(PlanData{i+1,1}-PlanData{i,1})./n;
pranformArea = pranformArea+Chords(i,j).*dist;
% fprintf('Chord: %f pranformArea: %f \n', Chords(i,j), pranformArea)
end
end
WetArea = Area *2;
pranformArea = pranformArea*2;
fprintf('Planform Area: %f, Wetted Area: %f \n', pranformArea, WetArea)
end
function Chords = findChords( n, PlanData )
Chord = cell2mat(PlanData(:,2));
X = cell2mat(PlanData(:,1));
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

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Matlab code/Legacy/Jacobi/WhettedAreaflubbed.m Executable file
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%function Area = WhettedArea( fileName, wingSpan )
function WhettedAreaflubbed(fileName,wingSpan, n)
% fileName = 'AirData.mat';
% wingSpan = 1;
% n = 50;
engineArea=600;
Area = 0;
pranformArea = 0;
cd('\\ad.uiuc.edu\ae\correa2\Desktop\AE441\Matlab code\Jacobi\Planforms')
[spans, chords, offsets, airfoil]=textread(fileName, '%f %f %f %s');
Chords = findChords(n, chords, spans);
cd('\\ad.uiuc.edu\ae\correa2\Desktop\AE441\Matlab code\Jacobi\Airfoils')
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)
cd('\\ad.uiuc.edu\ae\correa2\Desktop\AE441\Matlab code\Jacobi\')
end
function Chords = findChords( n, Chord, X )
% Chord = PlanData(:,2);
% X = PlanData(:,1);
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

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Matlab code/Legacy/MASTER441.bak2m Executable file
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%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(rootLOCATION)
for k = 1:length(variablenames)
eval([variablenames{k} '= variablevalues(k);']);
end
cd(airfoilLOCATION)
h1=13.33;
h2=10.5;
h3=9.5;
[sref swet]=WhettedArea(spans, chords, offsets, airfoil,n);
[planformLE planformTE]=plotpranform(spans, chords, offsets, airfoil, h1, 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);
cd(rootLOCATION)
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
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')
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, 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

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Matlab code/Legacy/MASTER441.m Executable file
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%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<AirfoilXupper(kU)
xFitU(1)=AirfoilXupper(kU-1);
xFitU(2)=AirfoilXupper(kU);
yFitU(1)=AirfoilYupper(kU-1);
yFitU(2)=AirfoilYupper(kU);
else
xFitU(1)=AirfoilXupper(kU);
xFitU(2)=AirfoilXupper(kU+1);
yFitU(1)=AirfoilYupper(kU);
yFitU(2)=AirfoilYupper(kU+1);
end
if xLoc<AirfoilXlower(kL)
xFitL(1)=AirfoilXlower(kL-1);
xFitL(2)=AirfoilXlower(kL);
yFitL(1)=AirfoilYlower(kL-1);
yFitL(2)=AirfoilYlower(kL);
else
xFitL(1)=AirfoilXlower(kL);
xFitL(2)=AirfoilXlower(kL+1);
yFitL(1)=AirfoilYlower(kL);
yFitL(2)=AirfoilYlower(kL+1);
end
aU = polyfit(xFitU, yFitU,1);
aL = polyfit(xFitL, yFitL,1);
% yplotLE(i,j) = a(1)*xplotLE(i,j)+a(2);
% thickness = AirfoilYupper(xLoc_indu)-AirfoilYlower(xLoc_indl);
thickness = (aU(1)*xLoc+aU(2))-(aL(1)*xLoc+aL(2));
end

31
Matlab code/Legacy/clreqcalc.m Executable file
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%ascorrea
%program to calculate required cl. valid up till 82345 ft
%from www.grc.nasa.gov/WWW/K-12/airplane/atmos.html
alt=input('Altitude (ft): ');
s=input('Input Wing Planform Area (sq.ft.): ');
v_mach=input('Input speed (Mach): ');
lift=input('Input required lift: ');
eloverdee=input('Input L/D requirement: ');
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;
cl_req=lift/(q*s);
fprintf('Cl_req: %f\n', cl_req);
cd_req=cl_req/eloverdee;
fprintf('Cd_req: %f\n', cd_req);

27
Matlab code/Legacy/dragbuildup.m Executable file
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%ascorrea
% FUCKA YOU EMPILICAR DATAR!!!
fprintf('Fuselage Data');
R_wf=input('\nInput Fuselage-wing Interference Factor (Fig 5.11):');
C_fr=input('Input Flat Plate Friction Coeff. Fuselage(Fig 5.13)');
fnratio=input('Input finesse ratio:');
S_wetf=input('Input Fuselage Wetted Area:');
fprintf('\nWing Data');
R_ls=input('\nInput Lifting Surface Correction Factor:');
C_fw=input('Input Flat Plate Friction Coeff. Wing(Fig 5.13)');
L_prime=input('Input Airfoil Thickness Location Factor:');
thickratio=input('Input Airfoil thickness (t/c):');
S_wetw=input('Input Wing Wetted Area:');
S_w=input('Input wing planform area:');
answer=input('\n\nCompressible? Yes (1) or No (2)');
if answer==1
M=input('Input Speed (Mach):');
c_fw=c_fw*(1-.09*M^2);
end
C_lw=input('Input lift Coeff.');
C_dof=R_wf*C_fr*(1+(60/fnratio^3)+.0025*fnratio)*(S_wetf)/(S_w);
C_dow=
fprintf('Cdo: %f', Cd)

83
Matlab code/Legacy/dragpolarpop.m Executable file
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%ascorrea
function dragpolar
count=1;
for answer=[1 2]
for answer2=[1 2 3]
% answer=input('Input Aviator (1), Sleak (2):');
% answer2=input('Take-off (1), Cruise (2), Landing (3):');
cd0Aviator=.01866;
cd0Sleak=.02056;
alphadeg=[-12:2:12];
alpha=(pi/180)*(alphadeg);
if answer==1
if answer2==1;
for i=1:length(alpha)
CL(i)=5.221144*(alpha(i))+.2581;
Cd(i)=cd0Aviator+CL(i)^2/(.8*pi()*10);
end
graphname='Drag Polar, Aviator, Take-off';
end
elseif answer==2
if answer2==1;
for i=1:length(alpha)
CL(i)=3.522567397*(alpha(i))+.4088;
CLcanard(i)=(4.122266*(alpha(i))+.4891)*(379.28/1496);
Cd(i)=cd0Sleak+CL(i)^2/(.8*pi()*7.9)+CLcanard(i)^2/(.8*pi()*7.831);
end
graphname='Drag Polar, Sleak, Take-Off';
end
if answer2==2;
for i=1:length(alpha)
CL(i)=2.887819338*(alpha(i))+.4007;
% Cd(i)=cd0Sleak+CL(i)^2/(.8*pi()*10);
CLcanard(i)=(3.819627*(alpha(i))+.4886)*(379.28/1496);
Cd(i)=cd0Sleak+CL(i)^2/(.8*pi()*7.9)+CLcanard(i)^2/(.8*pi()*7.831);
end
graphname='Drag Polar, Sleak, Cruise';
end
if answer2==3;
for i=1:length(alpha)
CL(i)=3.499816553*(alpha(i))+.3987;
% Cd(i)=cd0Sleak+CL(i)^2/(.8*pi()*10);
CLcanard(i)=(4.12721*(alpha(i))+.4891)*(379.28/1496);
Cd(i)=cd0Sleak+CL(i)^2/(.8*pi()*7.9)+CLcanard(i)^2/(.8*pi()*7.831);
end
graphname='Drag Polar, Sleak, landing';
end
else
error('Invalid Choice')
end
hold on
figure(count)
hold on
axisX0=linspace(0,max(cd));
axisY0=zeros(1,length(axisX0));
figure(count)
hold on
plot(axisX0, axisY0,'k--');
figure(count)
hold on
plot(Cd, CL);
figure(count)
hold on
plot(Cd, CL, '.');
title(graphname);
xlabel('C_d');
ylabel('C_L');
axis([0, .08, -1, 1.5]);
for i=1:length(alphadeg)
alphalabel=num2str(alphadeg(i));
label=[' \alpha =' alphalabel];
text(Cd(i), CL(i), label)
end
count=count+1;
end
end
end

48
Matlab code/Legacy/dragpolarpop2.m Executable file
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%ascorrea
function dragpolar
count=1;
cd0=input('Input cd0: ');
cl_alfa=input('Input cL_alfa(1/rad): ');
cL0=input('Input cL0: ');
sweep_LE=input('Input leading edge sweep (deg): ');
ar=input('Input aspect ratio: ');
cd_correction=input('Input Cd correction due to Transonic: ');
alphadeg=[-12:2];
alpha=(pi/180)*(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
figure(count)
hold on
axisX0=linspace(0,max(cd));
axisY0=zeros(1,length(axisX0));
figure(count)
hold on
plot(axisX0, axisY0,'k--');
figure(count)
hold on
plot(C_d, C_L);
figure(count)
hold on
plot(C_d, C_L, '.');
title(graphname);
xlabel('C_d');
ylabel('C_L');
axis([0, .08, -1, 1.5]);
for i=1:length(alphadeg)
alphalabel=num2str(alphadeg(i));
label=[' \alpha =' alphalabel];
text(C_d(i), C_L(i), label)
end
count=count+1;

24
Matlab code/Legacy/findcLalpha.m Executable file
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%ascorrea
AR=input('AR:');
M=input('Mach:');
clalpha=input('Cl alpha:');
sweep=input('Sweep at Max Thickness:');
sex=input('S exposed:');
sref=input('S reference:');
doverb=input('Finesse Ratio:');
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;
fprintf('CLalpha= %f\n', cLalpha);

13
Matlab code/Legacy/induceddrag.m Executable file
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@@ -0,0 +1,13 @@
%ascorrea
%calculates induced drag coefficient for LE sweep > 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);

35
Matlab code/Legacy/omkarshitty.m Executable file
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@@ -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

14
Matlab code/Legacy/penis.m Executable file
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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