Graph wont plot or show
1 vue (au cours des 30 derniers jours)
Afficher commentaires plus anciens
%load in data
%
clc
taredata=readmatrix('ATP_yaw0_pitchtare_clean_elev_down.csv');
taredata=taredata(1:12,:);
yawM5=readmatrix('ATP_yawM5_pitchsweep_clean_elev_down.csv')-taredata;
yawM10=readmatrix('ATP_yawM10_pitchsweep_clean_elev_down.csv')-taredata;
yawM15=readmatrix('ATP_yawM15_pitchsweep_clean_elev_down.csv')-taredata;
yaw0=readmatrix('ATP_yaw0_pitchsweep_clean_elev_down.csv')-taredata;
yaw5=readmatrix('ATP_yaw5_pitchsweep_clean_elev_down.csv')-taredata;
yaw10=readmatrix('ATP_yaw10_pitchsweep_clean_elev_down.csv')-taredata;
yaw15=readmatrix('ATP_yaw15_pitchsweep_clean_elev_down.csv')-taredata;
%slice it and take away tare forces
tare_forces=taredata(2:12,6:11);
yawM5_forces=yawM5(2:12,6:11);
yawM10_forces=yawM10(2:12,6:11);
yawM15_forces=yawM15(2:12,6:11);
yaw0_forces=yaw0(2:12,6:11);
yaw5_forces=yaw5(2:12,6:11);
yaw10_forces=yaw10(2:12,6:11);
yaw15_forces=yaw15(2:12,6:11);
%get alpha and beta for each
alpha_all=[yawM15(2:12, 12), yawM10(2:12, 12), yawM5(2:12, 12), yaw0(2:12, 12), yaw5(2:12, 12), yaw10(2:12, 12), yaw15(2:12, 12)]
beta_all =[yawM15(2:12, 13), yawM10(2:12, 13), yawM5(2:12, 13), yaw0(2:12, 13), yaw5(2:12, 13), yaw10(2:12, 13), yaw15(2:12, 13)]
%we have balance forces
%Fx Fy Fz
%we need to convert these to aircraft forces
%Xa Ya Za
%then convert to aerodynamic forces
%D S L
%pull balance forces from excel
fx_all=[yawM15_forces(:,2), yawM10_forces(:,2), yawM5_forces(:,2), yaw0_forces(:,2), yaw5_forces(:,2), yaw10_forces(:,2), yaw15_forces(:,2)]
fy_all=[yawM15_forces(:,3), yawM10_forces(:,3), yawM5_forces(:,3), yaw0_forces(:,3), yaw5_forces(:,3), yaw10_forces(:,3), yaw15_forces(:,3)]
fz_all=[yawM15_forces(:,1), yawM10_forces(:,1), yawM5_forces(:,1), yaw0_forces(:,1), yaw5_forces(:,1), yaw10_forces(:,1), yaw15_forces(:,1)]
%convert balance forces to aircraft forces
Xa_all=fx_all*(-1)
Ya_all=fy_all
Za_all=fz_all*(-1)
%get aerodynamic forces from aircraft force
D2=[((-Xa_all).*cos(beta_all).*cos(alpha_all))-((Ya_all).*sin(beta_all))-((Za_all).*cos(beta_all).*sin(alpha_all))]
S2=[((Xa_all).*sin(beta_all).*cos(alpha_all))-((Ya_all).*cos(beta_all))+((Za_all).*sin(beta_all).*sin(alpha_all))]
L2=[((Xa_all).*sin(alpha_all))-((Za_all).*cos(alpha_all))]
%get aerodynamic coefficients
q_inf2 = [yawM5(2:12,3), yawM10(2:12,3), yawM15(2:12,3), yaw0(2:12,3), yaw5(2:12,3), yaw10(2:12,3), yaw15(2:12,3)]
A = 0.4;
CD2 = D2./(q_inf2.*A)
CS2 = S2./(q_inf2.*A)
CL2 = (L2./(q_inf2.*A))
%make meaningful plots
%plot i was getting was linear
% create new alpha array with more data points
%create parabolic lift vs AoA graph
%create vector for aoa so ut can be plotted then fit data to parabola
CL_mean = mean(CL2, 2);
alpha_vec = [-15 -10 -7.5 -5 -2.5 0 2.5 5 7.5 10 15];
p = polyfit(alpha_vec, CL_mean, 1);
alpha_plot = linspace(-15, 15, 1000);
CL_parabola = polyval(p, alpha_plot);
figure;
plot(alpha_plot, CL_parabola);
xlabel('Angle of Attack (degrees)');
ylabel('Lift Coefficient (CL)');
title('Linear Fit of Lift Coefficient vs Angle of Attack');
drawnow;
saveas(gcf, 'figure.png')
1 commentaire
Walter Roberson
le 26 Mar 2023
We do not have your data files to test with.
After the code has run, show us the result of
nnz(~isfinite(CL_parabola))
Réponses (0)
Voir également
Catégories
En savoir plus sur Directed Graphs dans Help Center et File Exchange
Community Treasure Hunt
Find the treasures in MATLAB Central and discover how the community can help you!
Start Hunting!