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Copy pathSweep_taper_area_l.m
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Sweep_taper_area_l.m
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clear; close all; clc;
% APAME path
pathAPAME = '"F:\Universidad\Master_in_Aerospace_Engineering\TFM\Apame_v140915\ApameSolver\bin\apame_win64.exe"';
start = -14.8;
finish = 9.2;
span = 21.2347;
surf_lim = 150.4478;
factor = 1;
b = 0.7*2*span;
chord = surf_lim/(2*b);
vec = linspace(start,finish,3);
sweep_front_area = (0.3:0.04:0.7);
sweep_taper = (0.75:0.05:1);
data_APAME = zeros(length(vec),4,length(sweep_front_area),length(sweep_taper));
for kindex = 1:length(sweep_taper)
for jindex = 1:length(sweep_front_area)
close all
c_r1 = sweep_front_area(jindex)*surf_lim*2/(b*(1+sweep_taper(kindex)));
c_r2 = (1-sweep_front_area(jindex))*surf_lim*2/(b*(1+sweep_taper(kindex)));
c_t1 = sweep_taper(kindex)*c_r1;
c_t2 = sweep_taper(kindex)*c_r2;
N_bu = 10;
N_bl = 10;
N_bw = 2;
Finite = 0;
N_el = 30;
N = 5;
af_1r = '23012';
af_2r = '23012';
af_1t = '23012';
af_2t = '23012';
af_w = '0030';
AoS = 0;
height = 0;
[T,~,p,~] = atmosisa(height);
[rho,mu] = AirProperties(T-273.85, p/100, [],'rho', 'mu');
gamma = 1.4;
R_c = 287.04;
density = rho;
pressure = p;
wingspan = b;
lambda_1 = c_t1/c_r1;
lambda_2 = c_t2/c_r2;
surf_1 = 2*(c_r1+c_t1)*b/4;
surf_2 = 2*(c_r2+c_t2)*b/4;
surf = surf_1+surf_2;
MAC_1 = 2/3*c_r1*(1+lambda_1+lambda_1^2)/(1+lambda_1);
MAC_2 = 2/3*c_r2*(1+lambda_2+lambda_2^2)/(1+lambda_2);
MAC = (MAC_1*surf_1/surf+MAC_2*surf_2/surf);
h = 0.75*b*factor;
s = 1.6*MAC*factor;
R = 0.15*sqrt(h^2+s^2)*factor;
airspeed = 60;
Re = rho*MAC*airspeed/mu;
mach = airspeed/sqrt(gamma*R_c*T);
origin = [0 0 0];
method = 0;
err = 1e-7;
colldepth = 1e-7;
farfield = 5;
collcalc = 1;
velorder = 2;
results = 1;
requests = zeros(1,13); requests(1) = 1;
[Slices_Wing, Points_Wing] = ParametrizationBWFiniteTE(h,b,R,c_r1,c_r2,c_t1,c_t2,s,N_bu,N_bl,N_bw,N_el,N,Finite,af_1r,af_2r,af_1t,af_2t,af_w);
counter = 0;
for indAoA = vec
counter = counter + 1;
AoA = indAoA;
if indAoA < 0
name = append('BWAPAME_High_n',num2str(abs(indAoA)),'.inp');
APAME = append('BWAPAME_High_n',num2str(abs(indAoA)));
string = append('BWAPAME_High_n',num2str(abs(indAoA)),'.res');
else
name = append('BWAPAME_High_',num2str(indAoA),'.inp');
APAME = append('BWAPAME_High_',num2str(indAoA));
string = append('BWAPAME_High_',num2str(indAoA),'.res');
end
cases = [AoA; AoS];
[NoPan,area] = BoxWingAPAME(Slices_Wing,h,name,airspeed,density,pressure,mach,cases,wingspan,MAC,surf,origin,method,err,colldepth,farfield,collcalc,velorder,results,requests);
cmdname = 'command.txt';
cmdName = fopen(cmdname,'w');
fprintf(cmdName,APAME);
fclose(cmdName);
system(append(pathAPAME,' < command.txt'));
fileID = fopen(string,'r');
string_full = fscanf(fileID,'%s');
fclose(fileID);
index_CD = strfind(string_full,'CDRAG');
index_CD = index_CD+5;
value_CD = string_full(index_CD:index_CD+13);
value_CD = str2double(value_CD);
index_CL = strfind(string_full,'CLIFT');
index_CL = index_CL+5;
value_CL = string_full(index_CL:index_CL+13);
value_CL = str2double(value_CL);
data_APAME(counter,1,jindex,kindex) = AoA; data_APAME(counter,2,jindex,kindex) = value_CL; data_APAME(counter,3,jindex,kindex) = value_CD; data_APAME(counter,4,jindex,kindex) = NoPan;
end
end
end
[C_L_alpha,C_L_0,valid] = liftCurve(data_APAME);
save('EquivalentWingMEGAWESSweepTaperAreaLow.mat')
%% Plots
clear; close all; clc;
load('MEGAWESData.mat')
load('EquivalentWingMEGAWESSweepTaperAreaLow.mat')
figure()
hold on
plot(alpha,cL,'ok','LineWidth',2)
cL_a = (cL(end)-cL(1))/((finish-start)*pi/180);
cL_0 = interp1(alpha,cL,0);
vector = {'-b','--b','ob','-r','--r','or','-g','--g','og','-m','--m','om','-c','--c','oc','-y','--y','oy'};
for i = 1:jindex
for j = 1:kindex
C_L_APAME = data_APAME(:,2,i,j);
alpha_p = data_APAME(:,1,i,j);
err_abs(i,j) = sum(abs((cL(6:30)-C_L_APAME')./cL(6:30)));
if valid(i,j) == 1
plot(alpha_p,C_L_APAME,vector{i},'LineWidth',2)
[alpha_I,cL_I] = intersectionCurves(cL_a,cL_0,C_L_alpha(i,j),C_L_0(i,j));
Int(i,j) = liftDiffIntegral(alpha_I,cL,C_L_APAME,alpha_p*pi/180);
else
C_L_alpha(i,j) = NaN;
C_L_0(i,j) = NaN;
err_abs(i,j) = NaN;
Int(i,j) = NaN;
end
C_L_APAME = 0;
alpha_p = 0;
end
end
xlabel('\alpha','FontSize',14)
ylabel('C_L','FontSize',14)
set(gca,'FontSize',14)
[X,Y] = meshgrid(sweep_front_area*100,sweep_taper);
figure()
contourf(X,Y,Int')
hold on
% plot(span,cL_a,'xk','LineWidth',2)
xlabel('Relative fore wing area [%]','FontSize',14)
ylabel('\lambda','FontSize',14)
c = colorbar;
c.Label.String = 'I';
c.Label.FontSize = 14;
set(gca,'FontSize',14)
figure()
contourf(X,Y,C_L_alpha')
hold on
% plot(span,cL_a,'xk','LineWidth',2)
xlabel('Relative fore wing area [%]','FontSize',14)
ylabel('\lambda','FontSize',14)
c = colorbar;
c.Label.String = 'C_{L\alpha}';
c.Label.FontSize = 14;
set(gca,'FontSize',14)
figure()
contourf(X,Y,C_L_0')
hold on
% plot(span,cL_0,'xk','LineWidth',2)
xlabel('Relative fore wing area [%]','FontSize',14)
ylabel('\lambda','FontSize',14)
c = colorbar;
c.Label.String = 'C_{L0}';
c.Label.FontSize = 14;
set(gca,'FontSize',14)
function [C_L_alpha,C_L_0,valid] = liftCurve(data_APAME)
[a,b,c,d] = size(data_APAME);
for i = 1:c
for j = 1:d
C_L_APAME = data_APAME(:,2,i,j);
alpha_APAME = data_APAME(:,1,i,j);
[~,R1]=fit(alpha_APAME,C_L_APAME,'poly1');
[~,R2]=fit(alpha_APAME,C_L_APAME,'poly2');
C_L_alpha(i,j) = (C_L_APAME(end)-C_L_APAME(1))/((alpha_APAME(end)-alpha_APAME(1))*pi/180);
C_L_0(i,j) = interp1(alpha_APAME,C_L_APAME,0);
if R1.rsquare > 0.999 && C_L_alpha(i,j) < 10
valid(i,j) = 1;
else
valid(i,j) = 0;
end
end
end
end
function [x_I,y_I] = intersectionCurves(m1,n1,m2,n2)
x_I = (n1-n2)/(m2-m1);
y_I = m1*x_I+n1;
end
function I = liftDiffIntegral(alpha_I,cL,cL_A,alpha)
if alpha_I >= alpha(1) && alpha_I <= alpha(end)
I = (alpha_I-alpha(1))*(cL_A(1)-cL(6))/2 + (alpha(end)-alpha_I)*(cL_A(end)-cL(30))/2;
else
I = ((cL_A(1)-cL(6))+(cL_A(end)-cL(30)))*(alpha(end)-alpha(1))/2;
end
end