wing_param
% Original wing geometry
[t q2 q3]=size(latt_w.VORTEX);
figure(1)
hold on
plot3(latt_w.XYZ(:,:,1)',latt_w.XYZ(:,:,2)',latt_w.XYZ(:,:,3)','m*')
plot3(latt_w.XYZ(:,:,1)',latt_w.XYZ(:,:,2)',latt_w.XYZ(:,:,3)','r')


% for s=1:(t)
%    plot3(latt_w.COLLOC(s,1),latt_w.COLLOC(s,2),latt_w.COLLOC(s,3),'g*')
% end

axis equal
xlabel('Wing x-coordinate')
ylabel('Wing y-coordinate')
zlabel('Wing z-coordinate')
title('3-D Wing.')
grid on
hold off


wing_param3
cd output
fname=strcat(Run_ID(wing).name,'-Cx');
load(fname)
cd ..

% Delta cp plot
figure(2)
rotate3d on 
colormap(hot);
AAA=results.cp';
fill3(latt_w.XYZ(:,:,1)',latt_w.XYZ(:,:,2)',latt_w.XYZ(:,:,3)',AAA')
title('Delta cp distribution')
colorbar('vert')
axis equal

% Spanload ann Local CL Loading
figure(3)
subplot(2,1,1)
hold on, grid on
plot(results.ystation(:,1)/0.3048,results.ForcePerMeter(:,1)/4.44822162*0.3048);
Title('Spanload on main wing');
ylabel('lbf per foot');
xlabel('Spanstation')
hold off

subplot(2,1,2)
hold on, grid on
plot(results.ystation(:,1)/0.3048,results.CL_local(:,1),'r');
Title('Spanload on main wing');
ylabel('CL Local');
xlabel('Spanstation')
hold off

cd ..

% Airfoils
figure(5)
foil_axis=[0 1 -.08 .15];
load -ASCII ah94145.txt
af=ah94145;
subplot(3,1,1)
plot(af(:,1),af(:,2),'r')
set(findobj(gca,'Type','line','Color',[0 0 1]),'Color','red','LineWidth',5)
set(gca,'YTick',foil_axis(3:4))
set(gca,'YTickLabel',{'Lo','Hi'})
set(gca,'XTick',foil_axis(1:2))
set(gca,'XTickLabel',{'Leading Edge','Trailing Edge'})
title('AH94145 - Main Wing Airfoil');
axis(foil_axis)

subplot(3,1,2)
[x1 y1]=make_naca('0009',100,1);
plot(x1,y1,'r')
set(findobj(gca,'Type','line','Color',[0 0 1]),'Color','red','LineWidth',5)
set(gca,'YTick',foil_axis(3:4))
set(gca,'YTickLabel',{'',''})
set(gca,'XTick',foil_axis(1:2))
set(gca,'XTickLabel',{'Leading Edge','Trailing Edge'})
title('NACA 0009 - Horizontal Tail Airfoil');

subplot(3,1,3)
[x2 y2]=make_naca('0012',100,1);
plot(x2,y2,'r')
set(findobj(gca,'Type','line','Color',[0 0 1]),'Color','red','LineWidth',5)
set(gca,'YTick',foil_axis(3:4))
set(gca,'YTickLabel',{'',''})
set(gca,'XTick',foil_axis(1:2))
set(gca,'XTickLabel',{'Leading Edge','Trailing Edge'})
title('NACA 0012 - Vertical Tail Airfoil');