initial commit

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

Matlab code/Excel Files/FDR013.txt

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+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

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

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<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
+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 [wakeplot]=findwake(airfoil, chords, spans, offsets, n, alt, v_mach, laminarflow, width) 
+n=n/10;
+[q v_fps dynvisc]=findconstants(alt, v_mach);
+Chords = findChords(n, chords, spans);
+thicknessplot=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);
+
+        x=linspace(0, Chords(i,j));
+        
+        for k = 1:length(x)-1
+                thickness(k,j)=findthickness(airfoil{i}, Chords(i,j), x(k));
+            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
+        
+        
+
+thickness=[thicknessplot, wake];
+wakeplotX=[wakeplotX, wakeX];
+wakeplotY=[wakeplotY, wakeY];
+    end
+
+end
+thicknessplot(:,1)=[ ];
+wakeplotX(:,1)=[ ];
+wakeplotY(:,1)=[ ];
+wakeplot(1,:)=[0];
+flipud(thicknessplot);
+surf(wakeplotY, wakeplotX, thicknessplot)
+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
+end

Matlab code/Grimacelite.m

@@ -0,0 +1,257 @@
+%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 Grimacelite(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';
+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';
+airfoilLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Airfoils';
+pranformLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/XFLR Outputs/Trade Study planform';
+pranformConstraintLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/Planform Constraints';
+paramLOCATION='/Users/anthonyscorrea/Documents/MATLAB/AE441 - Home Edition/XFLR Outputs/Trade Study planform';
+%-----------------------------------------------------------------------]
+n=50;
+
+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);
+
+planformLE=[flipud(planformLE); -planformLE(:,1) planformLE(:,2)];
+planformTE=[flipud(planformTE); -planformTE(:,1) planformTE(:,2)];
+plotplan=[planformLE; flipud(planformTE);planformLE(1,:)];
+
+
+
+clf
+hold on
+plot(plotplan (:,1), plotplan(:,2), 'k', 'LineWidth', 2)
+axis equal
+axis off
+hold off
+cd(pranformLOCATION)
+filename=regexprep(pranformfile, '.plan', 'grimlite.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
+        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/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<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
+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
+end

Matlab code/Legacy/Jacobi/Airfoils/CB30015.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

Matlab code/Legacy/Jacobi/Planforms/AirData.dat

@@ -0,0 +1 @@
+0	0.610000000000000	0	n0011sc.dat

Matlab code/Legacy/Jacobi/Planforms/FDR001.avl

@@ -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	nasasc2-0714.dat
+34.77	15	60	nasasc2-0714.dat
+70	7.5	803	nasasc2-0714.dat

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

Matlab code/Legacy/Jacobi/WhettedArea.m

@@ -0,0 +1,54 @@
+%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

Matlab code/Legacy/Jacobi/WhettedAreaflubbed.m

@@ -0,0 +1,60 @@
+%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

Matlab code/Legacy/MASTER441.bak2m

@@ -0,0 +1,357 @@
+%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

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<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

Matlab code/Legacy/clreqcalc.m

@@ -0,0 +1,31 @@
+%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);

Matlab code/Legacy/dragbuildup.m

@@ -0,0 +1,27 @@
+%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)

Matlab code/Legacy/dragpolarpop.m

@@ -0,0 +1,83 @@
+%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

Matlab code/Legacy/dragpolarpop2.m

@@ -0,0 +1,48 @@
+%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;

Matlab code/Legacy/findcLalpha.m

@@ -0,0 +1,24 @@
+%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);

Matlab code/Legacy/induceddrag.m

@@ -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);

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

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

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<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

Matlab code/Ronaldplus.m

@@ -0,0 +1,539 @@
+%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)
+
+testrange={'20'};
+
+for testnumber=1:length(testrange)
+prefix='FDR0';
+name=strcat(prefix, testrange{testnumber});
+paramfile=strcat(name, '.param');
+pranformfile=strcat(name, '.plan');
+
+
+%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/Ronaldplus Outputs';
+%-----------------------------------------------------------------------]
+
+n=50;
+cd(paramLOCATION);
+[variablenames, variablevalues]=textread(paramfile, '%s %f');
+inputvalues=num2str(variablevalues);
+input=strcat(variablenames, inputvalues);
+[constantnames, constantvalues]=textread('constants.param', '%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
+
+for k = 1:length(constantnames)
+eval([constantnames{k} '= constantvalues(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 D_wing_to D_fuse_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 D_wing_cruise D_fuse_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 D_wing_loiter D_fuse_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 D_wing_landing D_fuse_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(outputsLOCATION)
+filenameplan=regexprep(pranformfile, '.plan', '_planform.tiff');
+filenameoutput=regexprep(pranformfile, '.plan', '.txt');
+plottitle=regexprep(pranformfile, '.plan', '');
+
+fid = fopen(filenameoutput, 'w');
+plottitle
+
+fprintf(fid, plottitle);
+
+
+
+fprintf(fid,'\nOutputs--------------------------------------------------\n');
+
+fprintf(fid, 'Wingspan: %f, AR: %f, Planform Area: %f, Wetted Area: %f \n', wingspan, AR, sref, swet);
+
+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(fid, '\n----------Cruise---------------------------------\n alfa: %f, Cd0: %f, CL: %f, CD: %f, D: %f,  CM: %f, L/D: %f \n D_Wing:%f, D_fuselage:%f', alphareq_cruise, cd0_cruise, cLreq_cruise, cD_cruise, D_cruise, cM_cruise, eloverdee_cruise, D_wing_cruise, D_fuse_cruise);
+
+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(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);
+fprintf(fid, '\nInputs--------------------------------------------------\n');
+for k=1:length(input)-1
+   fprintf(fid, '%s      %s \n',input{k}, input{k+1});
+end
+
+
+fclose(fid);
+cd(rootLOCATION)
+end
+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 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 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

Matlab code/airfoil.m

@@ -0,0 +1,24 @@
+%ASCorrea
+
+function airfoil(airfoilfilename)
+
+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';
+
+
+% airfoilfilename=input('Input airfoil dat file: \nNote: You must delete the header before using \n:','s');
+% airfoilfilename='flatplate.dat'
+cd(airfoilLOCATION)
+data=load(airfoilfilename);
+plottitle=regexprep(airfoilfilename, '.dat', '');
+
+dataX=data(:,1);
+dataY=data(:,2);
+
+plot(dataX, dataY, 'k', 'LineWidth', 2)
+axis equal
+axis off
+title(['Airfoil ' , plottitle])
+print ('-dtiff', plottitle)
+cd(rootLOCATION)
+end

Matlab code/strut/ARfit.m

@@ -0,0 +1,58 @@
+function [AR,xLE]=ARfit(P,t)
+
+global tmax
+% This function calculates the AR of a rectangle fitted inside an airfoil
+% described by the cubic spline function in P. The value t is the thickness
+% if the required rectangle (<t/c max).
+% OUTPUT:
+%                               AR=Aspect ratio of fitted rectangle
+%                               xLE=Forward x-position of rectangle.
+
+% Penalty functions for going out of bounds
+
+flag=0;
+x1=tmax/1000;
+if (t>tmax-x1)
+   tsave=t;
+   t=tmax-x1;
+   flag=2;
+  
+elseif (t<x1)
+        tsave=t;
+   t=x1;
+   flag=1;
+end;
+   
+N=50;
+theta=(pi-logspace(-1,pi,N))/2;
+theta(1)=[]; 
+theta=[fliplr(theta) pi-theta];
+f1=ppval(P,theta).*sin(theta)-t/2;
+f2=[f1(2:N*2-2) f1(N*2-2)];
+FF=abs(sign(f1)-sign(f2));
+roots=find(FF>0);
+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;

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

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

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

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

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

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;

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;

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

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;
+
+ 
+
+ 

Matlab code/strut/default.dat

@@ -0,0 +1,4 @@
+Strut length:
+4.0
+Strut width:
+1.5

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);

Matlab code/strut/e169.dat

@@ -0,0 +1,61 @@
+   1.00000  0.00000
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+   0.98598  0.00115
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+   1.00000  0.00000

Matlab code/strut/n0011sc.dat

@@ -0,0 +1,73 @@
+ 1.0000000 0.0000000
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+ 1.0000000 0.0000000

Matlab code/strut/profoil.xy

@@ -0,0 +1,121 @@
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+     .858469985282292200  -.036571096706810770
+     .878031579642266200  -.029870359517829740
+     .896712203003706900  -.023831183566654460
+     .914325006673737600  -.018490106411837240
+     .930700273472570900  -.013843493674984400
+     .945706851126577300  -.009881834320268800
+     .959218271069722000  -.006616851940244741
+     .971086173542466100  -.004058131331368275
+     .981145670975267700  -.002191944465334945
+     .989223412000137400  -.000970050936046449
+     .995149957201033200  -.000299711124549478
+     .998777486086403700  -.000039128734678850
+     .999999999999999800   .000000000000000049

Matlab code/strut/readme.txt

@@ -0,0 +1,69 @@
+
+**********************************************************************
+STRUT
+**********************************************************************
+
+Using the strut 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
+
+
+~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~

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);
+

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

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;

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;

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

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 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
+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 [plotY plotX thicknessplot]=findthicknessplot(airfoil, chords, spans, offsets, n, reso)
+    Chords = findChords(n, chords, spans);
+    thicknessplot=zeros(reso-1,1);
+    plotX=zeros(reso-1,1);
+    plotY=zeros(reso-1,1);
+    jcount=0;
+
+    for i=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);
+            
+            x=linspace(0, Chords(i,j),reso);
+            
+            for k = 1:length(x)-1
+%                
+%                 thickness(k,j)=findthickness(airfoil{i}, Chords(i,j), x(k));
+            end
+            wakeX(k,j)=x(k)+yplotLE(i,j);
+            wakeY(k,j)=y(j);
+            
+            for k = 1:length(x)-1
+                
+                wakeX(k,j)=x(k)+yplotLE(i,j);
+                wakeY(k,j)=y(j);
+            end
+            
+            
+            
+%             thicknessplot=[thicknessplot, thickness];
+            plotX=[plotX, wakeX];
+            plotY=[plotY, wakeY];
+        end
+        fprintf('Thickness plot: %6.2f percent complete\n', 100*(i+.1*j)/((length(chords)-1)+ n*.1))
+        
+    end
+    thicknessplot(:,1)=[ ];
+    plotX(:,1)=[ ];
+    plotY(:,1)=[ ];
+
+    flipud(thicknessplot);
+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 [wakeplot]=findwakeplot(chords, spans, alt, v_mach, laminarflow, width, n, reso) 
+[q v_fps dynvisc]=findconstants(alt, v_mach);
+Chords = findChords(n, chords, spans);
+wakeplot=zeros(reso,1);
+width=width/2;
+for i=1:1:(size(chords)-1)
+        dist=(spans(i+1)-spans(i))/n;
+    for j = 1:n
+        if (spans(i)+dist*j)>width
+            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

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 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
+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 [plotY plotX thicknessplot]=findthicknessplot(airfoil, chords, spans, offsets, n, reso)
+    Chords = findChords(n, chords, spans);
+    thicknessplot=zeros(reso-1,1);
+    plotX=zeros(reso-1,1);
+    plotY=zeros(reso-1,1);
+    jcount=0;
+
+    for i=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);
+            
+            x=linspace(0, Chords(i,j),reso);
+            
+            for k = 1:length(x)-1
+%                
+%                 thickness(k,j)=findthickness(airfoil{i}, Chords(i,j), x(k));
+            end
+            wakeX(k,j)=x(k)+yplotLE(i,j);
+            wakeY(k,j)=y(j);
+            
+            for k = 1:length(x)-1
+                
+                wakeX(k,j)=x(k)+yplotLE(i,j);
+                wakeY(k,j)=y(j);
+            end
+            
+            
+            
+%             thicknessplot=[thicknessplot, thickness];
+            plotX=[plotX, wakeX];
+            plotY=[plotY, wakeY];
+        end
+        fprintf('Thickness plot: %6.2f percent complete\n', 100*(i+.1*j)/((length(chords)-1)+ n*.1))
+        
+    end
+    thicknessplot(:,1)=[ ];
+    plotX(:,1)=[ ];
+    plotY(:,1)=[ ];
+
+    flipud(thicknessplot);
+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 [wakeplot]=findwakeplot(chords, spans, alt, v_mach, laminarflow, width, n, reso) 
+[q v_fps dynvisc]=findconstants(alt, v_mach);
+Chords = findChords(n, chords, spans);
+wakeplot=zeros(reso,1);
+width=width/2;
+for i=1:1:(size(chords)-1)
+
+        dist=(spans(i+1)-spans(i))/n;
+    for j = 1:n
+        if (spans(i)+dist*j)>width
+            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

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

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

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