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validate.m
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% SCRIPT "VALIDATE"
%
% Use to validate tornado results against outher sources:
% Select comparison with variable typeofrun
%
% #1 LIFTSLOPE VALIDATION
% #2 TAPER VALIDATION, Spanload check using monoplane equation,
% #3 Paneling validation, testing the different paneling schemes
% #4 NACA TN 1422 Validation Case
% #5 Test case, vo validation
% #6 NASA TN D-926
% #7 NACA RM R6K15
% #8 NACA0001 Airfoil comparison, XFOIL
% #9 Dihedral Validation
% #10 Dihedral Validation TN1732
% #11 Dihedral Validation TN1668 #1
% #12 Dihedral Validation TN1668 #2
% #13 Dihedral Validation TN1668 #3.1
% #14 Dihedral Validation TN1668 #3.2
% #15 Dihedral Validation TN1668 #3.3
% #16 NACA0008 FLAP Airfoil comparison
% #17 NASA TN4888 Propeller validation, figure 11b
%
% Set output=0 in the file config.m for a less chatty output.
%
% Version history
% Spånga, 2021-09-19: Updated to MATLAB R2020, TM
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
clear
typeofrun=17;
settings=config('startup');
switch typeofrun
%% LIFTSLOPE VALIDATION
case 0
results=[];
figure(1)
cd(settings.acdir)
load('ellipse');
if isfield(geo,'allmove');
else
geo.allmove= 0; %Allmoving surface set bit
geo.allmove_origin= [0 0 0]; %Origin of rotation for allmoving surface
geo.allmove_axis= [0 0 0]; %Hingeline for allmoving surface
geo.allmove_symetric= 0; %Symmetry for allmoving deflection
geo.allmove_def= 0; %Deflection of allmovin surface
end
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
state.alpha=1*pi/180;
quest=1; %Simple state solution, could be something else
%but then you'll have to change below too
JID='batchjob';
geo.nx=geo.nx*2;
nooftests=40;
%%%%%%%%%%
AR1=1:0.25:20;
const=2*pi*ones(size(AR1));
h=plot(AR1,const);
set(h,'Linewidth',2)
hold on
CLA=2*pi./(1+2./AR1);
h=plot(AR1,CLA); hold on;
set(h,'LineStyle','--','Linewidth',2)
AR2=0:0.25:3;
CLA2=pi/2*AR2;
h=plot(AR2,CLA2);
set(h,'LineStyle','-.','Linewidth',2)
%%%%%%%%%%%
B=geo.b*0.1;
for i=1:nooftests
geo.b=B*i;
[lattice,ref]=fLattice_setup2(geo,state,0);
AR(i)=ref.b_ref^2/ref.S_ref;
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
outdata1(i,1)=results.CL;
outdata2(i,2)=results.CD; %Save your outdata here
CLa(i)=outdata1(i,1)/(pi/180);
drawnow
end
plot(AR,CLa,'O');
title('Lift slope of an elliptic wing for different aspect ratios')
xlabel('Aspect Ratio, AR, [-]')
ylabel('Lift Slope, CL_\alpha')
legend('2D maximum','Lifting Line','Jones small AR','Tornado','Location','SouthEast')
%% TAPER VALIDATION
%Spanload check using monoplane equation,
case 1
figure(2)
for K=1:4
Taper=[1 0.6 0.4 0.1];
T=Taper(K);
alpha=4;
npos=100;
Cr=1;
Ct=T*Cr;
B=6.3/2;
AR=2*2*B/(Cr+Ct);
phi=(pi/2/npos:pi/2/npos:pi/2);
b=-cos(phi)*B;
t=(Cr-(-b./B*(Cr-Ct)))./Cr;
c=Cr*t;
a0=2*pi;
mu=c*a0./(2*AR*Cr*(1+T));
%monoplane equation
rhs=(mu*((alpha)*pi/180).*sin(phi))';
for i=1:npos
for j=1:npos
n=(2*j-1);
sn2(i,j)=sin(n*phi(i))*(n*mu(i)+sin(phi(i)));
end
end
A=sn2\rhs;
for i=1:npos
cld(i)=2*(1+T)/(pi*A(1)) * Cr/c(i) * sum(A'.*sin((1:2:(npos*2-1))*phi(i)));
end
plot(cos(phi),cld)
drawnow
hold on
%and then the tornado computation
cd(settings.acdir)
load('spantest');
if isfield(geo,'allmove');
else
geo.allmove= 0; %Allmoving surface set bit
geo.allmove_origin= [0 0 0]; %Origin of rotation for allmoving surface
geo.allmove_axis= [0 0 0]; %Hingeline for allmoving surface
geo.allmove_symetric= 0; %Symmetry for allmoving deflection
geo.allmove_def= 0; %Deflection of allmovin surface
end
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
geo.ny=10;
geo.nx=3;
geo.b=B;
geo.meshtype=4;
geo.T=T;
quest=1; %Simple state solution, could be something else
results=[]; %but then you'll have to change below too
JID='batchjob';
[lattice,ref]=fLattice_setup2(geo,state,2);
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
lcl=results.CL_local./results.CL;
lsp=results.ystation/geo.b;
lemma=size(lsp,1)/2;
plot(lsp((lemma+1):1:end),lcl((lemma+1):1:end),'k*')
xlabel('Spanstation, y/S, [-]')
ylabel('Normalized lift, C_l/C_L, [-]')
end
legend('Monoplane equation','Tornado','location','south')
text(0.3,0.3,'Taper = 1, 0.6, 0.4, 0.1 respectively')
%% DIHEDRAL VALIDATION
%% C172 VALIDATION
case 2 %Cant get this to match properly just yet.
figure(3)
% Data from L.L. Leisher et al, Stability derivatives of Cessna aircraft, Cessna
% Aircraft Company, 1957.
CL=0.386;
CD=0.042;
CL_a=4.41;
CD_a=0.182;
Cm_a=-0.409;
Cm_de=-1.099;
CY_b=-0.35;
Cl_b=0.103; %Change sign due to different convensions
Cn_b=-0.0583; %Change sign due to different convensions
CY_p=0.0925; %Change sign due to different convensions
Cl_p=-0.483;
Cn_p=-0.035;
CY_r=-0.175; %Change sign due to different convensions
Cl_r=-0.1; %Change sign due to different convensions
Cn_r=-0.086; %Change sign due to different convensions
Cl_da=0.229;
Cn_da=0.027;
Cn_dr=-0.0539;
%%%%%%%%%%%%%
cd(settings.acdir)
load('test2');
if isfield(geo,'allmove');
else
geo.allmove= 0; %Allmoving surface set bit
geo.allmove_origin= [0 0 0]; %Origin of rotation for allmoving surface
geo.allmove_axis= [0 0 0]; %Hingeline for allmoving surface
geo.allmove_symetric= 0; %Symmetry for allmoving deflection
geo.allmove_def= 0; %Deflection of allmovin surface
end
cd(settings.hdir)
cd(settings.sdir)
load('cessnastate');
cd(settings.hdir)
state.AS=state.AS*2;
results=[];
quest=1; %Simple state solution, could be something else
%but then you'll have to change below too
JID='batchjob';
geo.nx=geo.nx;
geo.ny=geo.ny;
[lattice,ref]=fLattice_setup2(geo,state,1);
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
%quest=8; %Central Differernce
%solverloop5(results,quest,JID,lattice,state,geo,ref);
%cd(settings.odir)
% load batchjob-Cxx_diff;
%cd(settings.hdir)
A=[ CL results.CL
CD results.CD
CL_a results.CL_a
CD_a results.CD_a
Cm_a results.Cm_a
Cm_de results.Cm_d(3)
CY_b results.CY_b
Cl_b results.Cl_b
Cn_b results.Cn_b
CY_p results.CY_P
Cl_p results.Cl_P
Cn_p results.Cn_P
CY_r results.CY_R
Cl_r results.Cl_R
Cn_r results.Cn_R
Cl_da results.Cl_d(2)
Cn_da results.Cn_d(2)
Cn_dr results.Cn_d(4)];
subplot(2,1,1)
h=bar(A,0.75,'grouped');
h2=gca;
set(h2,'XTick',1:1:18);
set(h2,'XTickLabel',{'CL','CD','CL_a','CD_a','Cm_a','Cm_de','CY_b','Cl_b'...
,'Cn_b','CY_P','Cl_P','Cn_P','CY_R','Cl_R','Cn_R','Cl_da','Cn_da','Cn_dr'});
subplot(2,1,2)
B=diff(abs(A)')';
err=B./A(:,1);
bar(err);
h2=gca;
set(h2,'XTick',1:1:18);
set(h2,'XTickLabel',{'CL','CD','CL_a','CD_a','Cm_a','Cm_de','CY_b','Cl_b'...
,'Cn_b','CY_P','Cl_P','Cn_P','CY_R','Cl_R','Cn_R','Cl_da','Cn_da','Cn_dr'});
%% Paneling validation, testing the different paneling schemes
case 3
for i=1:4
cd(settings.acdir)
load('spantest');
if isfield(geo,'allmove');
else
geo.allmove= 0; %Allmoving surface set bit
geo.allmove_origin= [0 0 0]; %Origin of rotation for allmoving surface
geo.allmove_axis= [0 0 0]; %Hingeline for allmoving surface
geo.allmove_symetric= 0; %Symmetry for allmoving deflection
geo.allmove_def= 0; %Deflection of allmovin surface
end
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
geo.ny=10;
geo.nx=5;
geo.b=3;
geo.meshtype=i; %<----- set paneling
geo.T=0.6;
quest=1; %Simple state solution, could be something else
results=[]; %but then you'll have to change below too
JID='batchjob';
[lattice,ref]=fLattice_setup2(geo,state,0);
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
lcl=results.CL_local./results.CL;
lsp=results.ystation/geo.b;
RXZ={'kx-', 'r*--', 'gd-.','m+:'};;
lemma=size(lsp,1)/2;
figure(4)
%plot(lsp((lemma+1):1:end),lcl((lemma+1):1:end),RXZ(i))
h=plot(lsp,lcl,cell2mat(RXZ(i)));
set(h,'Linewidth',2)
title('Spanload with different paneling schemes.')
xlabel('Spanstation, y/S, [-]')
ylabel('Normalized lift, C_l/C_L, [-]')
hold on
%geometryplot(lattice,geo,ref);
hold on
end
legend('Linear','Half cosine in y','Cosine in x, half cosine in y','Cosine in x, cosine in y','Location','South')
%% NACA TN 1422 Validation Case
case 4
%Experimental Data
%ex.alpha=[-3 -2 -0.8 0.1 1.3 2.3 3.6 4.5 5.5 6.5 7.6 8.4 9.8 10.8 11.5 12 12.4 13 13.5 14 14.5 15 15.6 15.7];
%ex.CL=[-0.19 -0.09 0 0.1 0.19 0.28 0.37 0.46 0.55 0.63 0.74 0.82 0.91 1.01 1.05 1.1 1.13 1.19 1.23 1.26 1.31 1.34 1.35 1.03];
%ex.CD=0.001*[8 6 5 5 6 8 10 15 19 24 28 35 42 50 54 58 62 66 71 76 81 85 90 118];
%ex.CD0=0.001*[6.2 6 5 4.5 4.3 4.5 5.5 6.8 7.5 8.2 8.8 10.1 12 13]
ex.CD=[40 35 30 28 30 42 58 80 100 130 158 194 230 276 292 320 348 362 389 420 448 470 500 645]*0.1/550;
ex.CD0=[175 158 140 123 120 123 140 190 210 230 245 280 315 345].*0.016/440;
ex.CL=[10 60 112 164 218 270 320 364 413 460 520 565 618 668 688 712 732 760 785 806 830 850 854 680]*1.4/770-0.2;
ex.alpha=[30 60 85 115 145 175 206 233 262 291 320 350 380 410 425 440 453 468 484 500 510 525 540 540]*20/553-4;
ex.y=[0 1 2 3 4 5 6 6.5 7 7.5 8 8.5 9 9.5]*0.1;
ex.Cl=[1.3 1.35 1.38 1.4 1.42 1.43 1.42 1.41 1.39 1.37 1.34 1.3 1.2 1.03];
x=ex.CL(8:end);
ex.extrap.CD0 = 0.0084*x.^2 - 0.0023*x + 0.0062;
ex.CD0comp=[ex.CD0(1:8) ex.extrap.CD0(2:end)];
cd(settings.acdir)
load('NACATN1422');
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
geo.nx=10;
geo.ny=10;
j=0;
R=[];
stallCl=[];
for i=1:21; %Angle of attack
alpha=(-3:1:20)*pi/(180);
alpha(19)=14.9*pi/180; %Stall angle
state.alpha=alpha(i);
quest=1; %Simple state solution, could be something else
results=[]; %but then you'll have to change below too
JID='batchjob';
[lattice,ref]=fLattice_setup2(geo,state,0);
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
results=trefftz5(results,state,geo,lattice,ref);
R.alpha(i)=state.alpha;
R.CL(i)=results.CL;
R.CD(i)=results.CD;
R.Cm(i)=results.Cm;
R.CLL(i,:)=results.CL_local;
R.YS(i,:)=results.ystation;
R.TDC(i)=results.Trefftz_drag_Coeff;
%figure(6)
%plot(results.ystation,results.CL_local)
%hold on
indx=find(results.CL_local>1.44);
if isempty(indx)==0;
disp('STALL ONSET')
j=j+1;
%plot(results.ystation(indx),results.CL_local(indx),'r*')
stalledalpha(j)=state.alpha;
stallCl(j,:)=results.CL_local;
stallCL(j)=results.CL;
break
end
end
figure(6)
h1=plot(results.ystation./(0.5*ref.b_ref),stallCl(1,:))
hold on
h2=plot(results.ystation(indx)./(0.5*ref.b_ref),stallCl(1,indx) ,'r*')
h4=plot(ex.y,ex.Cl,'O');
h3=plot([0.2 0.6],[1.44 1.44],'r');
set(h1,'Linewidth',2);
set(h2,'Linewidth',2);
set(h3,'Linewidth',2);
set(h3,'Linewidth',2);
title('Lift distribution, NACA TN 1422, first case.')
xlabel('Spanstation, 2y/b, [-]')
ylabel('Local lift cofficient, C_l, [-]')
legend('Tornado','Stalled panels','Experimental distribution','Experimental stall position')
axis([0 1 0.6 1.6]);
grid
CLa=sum(diff(R.CL))/(size(R.CL,2)-1)
A=[ones(size(R.CL))' R.CL'];
aLO=A\R.alpha';
Alpha_LO=aLO(1)*180/pi
STL=min(stalledalpha)*180/pi;
figure(5)
h=plot(R.alpha*180/pi,R.CL);
hold on
h2=plot(ex.alpha,ex.CL,'O');
h3=plot([STL STL],[0 1.5],'r:');
set(h,'Linewidth',2)
set(h2,'Linewidth',2)
set(h3,'Linewidth',2)
title('Lift curve, NACA TN 1422, first case.')
xlabel('Angle of Attack, alpha, [deg]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Tornado','Experiment','Tornado stall onset predicition',2)
grid
figure(7)
h1=plot(ex.CD-ex.CD0comp,ex.CL,'O');
hold on
h2=plot(R.CD,R.CL);
h3=plot(R.TDC,R.CL,'r');
set(h1,'Linewidth',2);
set(h2,'Linewidth',2);
set(h3,'Linewidth',2);
title('Polar, NACA TN 1422, first case.')
xlabel('Induced Drag Cofficient, C_Di, [-]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Experiment','Tornado','Tornado Trefftz corrected',4)
grid
%% Test case, vo validation
case 5
cd(settings.acdir)
load('NACATN1422');
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
j=0;
R=[];
stallCl=[];
imax=25;
for i=1:imax;
i
alpha=10.8282*pi/180;
geo.nx=10;
geo.ny=i;
geo.b=90;
geo.meshtype=2;
state.AS=60;
state.pgcorr=1;
state.alpha=alpha;
quest=1; %Simple state solution, could be something else
results=[]; %but then you'll have to change below too
JID='batchjob';
[lattice,ref]=fLattice_setup2(geo,state,0);
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
results=trefftz5(results,state,geo,lattice,ref);
R.TDC(i)=results.Trefftz_drag_Coeff;
%R.alpha(i)=state.alpha;
R.CL(i)=results.CL;
R.CD(i)=results.CD;
R.Cm(i)=results.Cm;
end
figure(8)
h=plot([1 geo.nx*imax],[0.0376 0.0376],'g');
set(h,'Linewidth',2);
hold on
h=plot(geo.nx*(1:imax),R.TDC,'r');
set(h,'Linewidth',2);
h=plot(geo.nx*(1:imax),R.CD,'b');
set(h,'Linewidth',2);
xlabel('Number of panels.')
ylabel('Induced drag coefficient, CD_i')
title('Naca TN1422, case #1, 10 degree AoA')
axis([0 geo.nx*imax 0 max(R.TDC)])
legend('Experimantal','Trefftz','Tornado')
grid
%% NASA TN D-926
case 6
disp('NASA TN D-926')
%ex.alpha=[-10 -6 -4 -2 0 2 4 6 8 10 12 14 16 18];
%ex.CL=[2 14 20 26 33 41 48.5 56 63 70 78.5 87 93 100]*1/100;
%ex.CD=[3 3.5 4 5 6.1 7.5 9.5 11.5 14 16.5 19.9 24 28 39]*1/100;
ex.alpha=[-10 -8 -6 -3.8 -1.8 0.4 2.5 4.6 6.7 8.8 10.8 12.9 14.9 17];
ex.CL=[8 18 31 44 60 73 85 98 112 125 138 144 149 149]*1/100;
ex.CD=[2.4 2.5 2.6 3 4 5.6 7.5 9 11.5 14 17 20 24 30]*1/100;
cd(settings.acdir)
load('NASATND926');
if isfield(geo,'allmove');
else
geo.allmove= 0; %Allmoving surface set bit
geo.allmove_origin= [0 0 0]; %Origin of rotation for allmoving surface
geo.allmove_axis= [0 0 0]; %Hingeline for allmoving surface
geo.allmove_symetric= 0; %Symmetry for allmoving deflection
geo.allmove_def= 0; %Deflection of allmovin surface
end
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
j=0;
geo.nx=[10];
geo.ny=[20];
geo.b=2;
for i=1:20; %Angle of attack
alpha=(-12:2:20)*pi/(180);
alpha(19)=14.9*pi/180; %Stall angle
state.alpha=alpha(i);
quest=1; %Simple state solution, could be something else
results=[]; %but then you'll have to change below too
JID='batchjob';
[lattice,ref]=fLattice_setup2(geo,state,0);
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
results=trefftz5(results,state,geo,lattice,ref);
R.alpha(i)=state.alpha;
R.CL(i)=results.CL;
R.CD(i)=results.CD;
R.Cm(i)=results.Cm;
R.CLL(i,:)=results.CL_local;
R.YS(i,:)=results.ystation;
R.TDC(i)=results.Trefftz_drag_Coeff;
%figure(6)
%plot(results.ystation,results.CL_local)
%hold on
indx=find(results.CL_local>1.42);
if isempty(indx)==0;
disp('STALL ONSET')
j=j+1;
%plot(results.ystation(indx),results.CL_local(indx),'r*')
stalledalpha(j)=state.alpha;
stallCl(j,:)=results.CL_local;
stallCL(j)=results.CL;
break
end
end
STL=min(stalledalpha)*180/pi;
figure(9)
h=plot(R.alpha*180/pi,R.CL);
hold on
h2=plot(ex.alpha,ex.CL,'O');
h3=plot([STL STL],[0 1.5],'r:');
set(h,'Linewidth',2)
set(h2,'Linewidth',2)
set(h3,'Linewidth',2)
title('Lift curve, NACA TND 926, AR=4.')
xlabel('Angle of Attack, alpha, [deg]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Tornado','Experiment','Tornado stall onset predicition')
grid
figure(10)
experimentalCD0=0.024;
h1=plot(ex.CD-experimentalCD0,ex.CL,'O');
hold on
h2=plot(R.CD,R.CL);
h3=plot(R.TDC,R.CL,'r-.');
set(h1,'Linewidth',2);
set(h2,'Linewidth',2);
set(h3,'Linewidth',2);
title('Polar, NACA TND 926, AR=4.')
xlabel('Induced Drag Cofficient, C_Di, [-]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Experiment','Tornado','Trefftz plane')
grid
%% NACA RM R6K15
case 7
disp('NACA RM R6K15')
cd(settings.acdir)
load('NACATMR6K15');
if isfield(geo,'allmove');
else
geo.allmove= 0; %Allmoving surface set bit
geo.allmove_origin= [0 0 0]; %Origin of rotation for allmoving surface
geo.allmove_axis= [0 0 0]; %Hingeline for allmoving surface
geo.allmove_symetric= 0; %Symmetry for allmoving deflection
geo.allmove_def= 0; %Deflection of allmovin surface
end
cd(settings.hdir)
cd(settings.sdir)
load('teststate');
cd(settings.hdir)
S1=[ -3.2975 -0.1247 0.0233 -0.0109
0.1434 0.0260 0.0233 0
2.5806 0.1356 0.0215 0.0181
4.9462 0.2486 0.0286 0.0159
9.3190 0.4507 0.0483 0.0210
13.0466 0.6356 0.0769 0.0196
16.1290 0.7521 0.1342 -0.0152
18.9247 0.8925 0.1932 -0.0051
21.3620 0.9678 0.2379 0.0029
23.7276 1.0363 0.2987 0.0065
25.8781 1.0705 0.4007 0.0239
29.4624 1.0877 0.5403 0.0355
31.5412 1.0877 0.6100 0.0500];
S2=[ -2.9243 -0.1312 0.0311 0.0053
0.2463 0.0561 0.0260 0.0032
3.4170 0.2467 0.0260 -0.0044
6.3808 0.4307 0.0363 -0.0100
9.6204 0.6245 0.0501 -0.0170
12.6532 0.8085 0.0725 -0.0233
16.0306 0.9991 0.1225 -0.0219
18.5809 1.1010 0.1811 -0.0086
20.8555 1.1634 0.2241 -0.0024
22.5786 1.1831 0.3069 -0.0003
24.9222 1.0681 0.3999 -0.0017
28.9199 0.9695 0.4981 0.0018];
S3=[ -1.9679 -0.0707 0.0391 -0.0266
0.1111 0.0447 0.0340 -0.0286
2.1900 0.1940 0.0323 -0.0296
4.2019 0.3331 0.0391 -0.0316
6.2808 0.4723 0.0441 -0.0327
8.3598 0.6012 0.0543 -0.0332
10.3046 0.7403 0.0695 -0.0337
12.3836 0.8760 0.0847 -0.0337
14.3954 1.0220 0.1049 -0.0337
15.6026 1.0898 0.1167 -0.0332
16.6085 1.1475 0.1252 -0.0322
17.6815 1.2086 0.1404 -0.0322
18.5533 1.2697 0.1522 -0.0266
19.6263 1.3240 0.1691 -0.0256
20.7664 1.3715 0.1775 -0.0286
21.7053 1.2595 0.2451 0.0053];
S4=[-3.3492 -0.1708 0.0279 0.0007
-0.1154 0.0378 0.0245 0.0095
2.1078 0.1824 0.0245 0.0169
4.2637 0.3237 0.0296 0.0223
6.4869 0.4718 0.0363 0.0284
8.5080 0.6097 0.0481 0.0324
10.5964 0.7376 0.0565 0.0364
12.6849 0.8688 0.0768 0.0412
14.7734 1.0000 0.0953 0.0432
15.7165 1.0437 0.1037 0.0438
16.7271 1.1110 0.1172 0.0452
17.7376 1.1581 0.1290 0.0465
18.7482 1.2220 0.1391 0.0479
20.0956 1.2859 0.1559 0.0479
21.1735 1.2355 0.2233 0.0129
22.6556 1.1884 0.2873 0.0061];
S5=[-3.0427 -0.1484 0.0250 -0.0020
0.1148 0.0347 0.0194 0.0067
2.1708 0.1460 0.0194 0.0082
3.1254 0.2071 0.0194 0.0119
4.4472 0.2753 0.0250 0.0155
6.2829 0.3794 0.0286 0.0199
8.5592 0.5087 0.0379 0.0243
9.4404 0.5518 0.0415 0.0272
12.4510 0.7062 0.0636 0.0382
15.5350 0.8786 0.0913 0.0514
18.7659 1.0581 0.1318 0.0806
20.7485 1.1263 0.2129 0.0763
22.7311 1.1694 0.2866 0.0587
24.6403 1.2053 0.3897 0.0353
26.6229 1.2305 0.4966 0.0214
28.6789 1.2018 0.5316 0.0294
29.7803 1.1623 0.5518 0.0492];
j=0;
geo.nx=[5];
geo.ny=[10];
%geo.b=2;
T=[0.38 0.4 0.55 0.44 0.42];
b=[32.38 36.39 30.53 36.06 33.56]*0.5*0.3;
c=[15.4 11.34 8.71 10.59 13.34]*0.3;
SW=[-45 -30 0 30 45]*pi/180;
refp=[-2.9 -1.5 2.27 7.25 10.71]*0.3;
for j=1:5
geo.ref_point=[refp(j) 0 0];
geo.b=b(j);
geo.T=T(j);
geo.c=c(j);
geo.SW=SW(j);
wingx(j,:)=[0 0.25*geo.c+geo.b*tan(geo.SW)-0.25*geo.T*geo.c 0.25*geo.c+geo.b*tan(geo.SW)+0.75*geo.T*geo.c geo.c]./geo.c;
wingy(j,:)=[0 geo.b geo.b 0]./geo.c;
wingz(j,:)=[0 0 0 0]./geo.c;
figure(20)
subplot(3,2,1)
plot3(wingx(j,:)+1.2*j,wingy(j,:),wingz(j,:),'k');
hold on
plot3(wingx(j,:)+1.2*j,-wingy(j,:),wingz(j,:),'k');
axis equal
axis off
for i=1:16; %Angle of attack
alpha=(-4:2:26)*pi/(180);
state.alpha=alpha(i);
quest=1; %Simple state solution, could be something else
results=[]; %but then you'll have to change below too
JID='batchjob';
[lattice,ref]=fLattice_setup2(geo,state,1);
%if i==1
% geometryplot(lattice,geo,ref);
%end
solverloop5(results,quest,JID,lattice,state,geo,ref);
cd(settings.odir)
load batchjob-Cx;
cd(settings.hdir)
% results=trefftz5(results,state,geo,lattice,ref);
R.alpha(j,i)=state.alpha;
R.CL(j,i)=results.CL;
R.CD(j,i)=results.CD;
R.Cm(j,i)=results.Cm;
% R.CLL(j,i,:)=results.CL_local;
% R.YS(j,i,:)=results.ystation;
% R.TDC(j,i)=results.Trefftz_drag_Coeff;
end
end
a(1)=sum(diff(S1(1:6,2))./(diff(S1(1:6,1))*pi/180))/5;
a(2)=sum(diff(S2(1:6,2))./(diff(S2(1:6,1))*pi/180))/5;
a(3)=sum(diff(S3(1:6,2))./(diff(S3(1:6,1))*pi/180))/5;
a(4)=sum(diff(S4(1:6,2))./(diff(S4(1:6,1))*pi/180))/5;
a(5)=sum(diff(S5(1:6,2))./(diff(S5(1:6,1))*pi/180))/5;
b(1)=sum(diff(R.CL(1,1:6))./(diff(R.alpha(1,1:6))))/5;
b(2)=sum(diff(R.CL(2,1:6))./(diff(R.alpha(2,1:6))))/5;
b(3)=sum(diff(R.CL(3,1:6))./(diff(R.alpha(3,1:6))))/5;
b(4)=sum(diff(R.CL(4,1:6))./(diff(R.alpha(4,1:6))))/5;
b(5)=sum(diff(R.CL(5,1:6))./(diff(R.alpha(5,1:6))))/5;
sweep=[-45 -30 0 30 45];
rerr=(b-a)./a;
figure(17)
subplot(2,1,1)
bar( [a' b'], 'group')
xlabel('Wing Sweep, \Lambda, [deg]')
ylabel('Liftslope, a, [1/rad]')
legend('Experiments','Tornado','Location','South')
title('Comparison between experimental and numerical linear liftslope.')
subplot(2,1,2)
bar(rerr)
xlabel('Wing Sweep, \Lambda, [deg]')
ylabel('Liftslope relative error, err, [-]')
figure(12)
h=plot(R.alpha(1,:)*180/pi,R.CL(1,:));
hold on
h2=plot(S1(:,1),S1(:,2),'O');
set(h,'Linewidth',2)
set(h2,'Linewidth',2)
title('Lift curve, NACA TM R6K15, Sweep=-45.')
xlabel('Angle of Attack, alpha, [deg]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Tornado','Experiment')
grid
axes('position',[0.55 0.14 0.3 0.3])
h=plot(wingy(1,:),-wingx(1,:),'k');
set(h,'Linewidth',3)
hold on
h=plot(-wingy(1,:),-wingx(1,:),'k');
set(h,'Linewidth',3)
h = annotation('arrow',[0.7 0.7],[0.4 .2]);
set(h,'Linewidth',2)
axis equal
axis off
%--------------------
figure(13)
h=plot(R.alpha(2,:)*180/pi,R.CL(2,:));
hold on
h2=plot(S2(:,1),S2(:,2),'O');
set(h,'Linewidth',2)
set(h2,'Linewidth',2)
title('Lift curve, NACA TM R6K15, Sweep=-30.')
xlabel('Angle of Attack, alpha, [deg]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Tornado','Experiment')
grid
axes('position',[0.55 0.14 0.3 0.3])
h=plot(wingy(2,:),-wingx(2,:),'k');
set(h,'Linewidth',3)
hold on
h=plot(-wingy(2,:),-wingx(2,:),'k');
set(h,'Linewidth',3)
h = annotation('arrow',[0.7 0.7],[0.4 .2]);
set(h,'Linewidth',2)
axis equal
axis off
%--------------------
figure(14)
h=plot(R.alpha(3,:)*180/pi,R.CL(3,:));
hold on
h2=plot(S3(:,1),S3(:,2),'O');
set(h,'Linewidth',2)
set(h2,'Linewidth',2)
title('Lift curve, NACA TM R6K15, Sweep=0.')
xlabel('Angle of Attack, alpha, [deg]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Tornado','Experiment')
grid
axes('position',[0.55 0.14 0.3 0.3])
h=plot(wingy(3,:),-wingx(3,:),'k');
set(h,'Linewidth',3)
hold on
h=plot(-wingy(3,:),-wingx(3,:),'k');
set(h,'Linewidth',3)
h = annotation('arrow',[0.7 0.7],[0.4 .2]);
set(h,'Linewidth',2)
axis equal
axis off
%--------------------
figure(15)
h=plot(R.alpha(4,:)*180/pi,R.CL(4,:));
hold on
h2=plot(S4(:,1),S4(:,2),'O');
set(h,'Linewidth',2)
set(h2,'Linewidth',2)
title('Lift curve, NACA TM R6K15, Sweep=30.')
xlabel('Angle of Attack, alpha, [deg]')
ylabel('Lift Cofficient, C_L, [-]')
legend('Tornado','Experiment')