wing_param3

% COPUTATIONS AND RESULTS
% [1]. Simple solution computation. Forces/Coefficients only
%  
% [2]. Alpha sweep computation 
% [3]. Beta sweep computation 
% [4]. Delta sweep computation 
%  
% [5]. Roll rate sweep computation 
% [6]. Pitch rate sweep computation 
% [7]. Yaw rate sweep computation 
%  
% [8]. Central difference expansion around current state

% geometryplot(latt_w(wing),geometry(wing),ref_w(wing))
% solverloop5(results,computation,Run_ID(wing).name,latt_w(wing),flight_con,geometry(wing),ref_w(wing));
% resultplot2(1,Run_ID(wing).name)

for wing=1:length(taper(1,:))
    figure(wing)
    clf
    set(gcf,'Position',[10 10 1250 750])
    
    subplot(3,2,1)
    plot(latt_w(wing).XYZ(:,:,2)'/0.3048,latt_w(wing).XYZ(:,:,1)'/0.3048,'k')
    axis equal,hold on
    xlabel('Wing x-coordinate')
    ylabel('Wing y-coordinate')
    zlabel('Wing z-coordinate')
    title('3-D Wing configuration')
    axis tight
    grid on
    hold off
    
  cd output
    fname=strcat(Run_ID(wing).name,'-Cx');
    load(fname)
    cd ..
    
    subplot(3,2,3)
    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(3,2,5)
    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 output
    fname=strcat(Run_ID(wing).name,'-Cxx_diff');
    load(fname)
    cd ..     
    
    subplot(3,2,[2 4 6])
    axis off
    text(0,1,'TORNADO CALCULATION RESULTS, Central difference')
text(0,.95,'JID: '); text(0.25,0.95,Run_ID(wing).name)
text(0,.90,'Ref. Area: ');	text(0.25,0.90,num2str(ref_w(wing).S_ref/0.3048^2 ));	
text(0,.85,'Root chord: ');text(0.25,.85,num2str(geometry(wing).c/0.3048));
text(0,.8,'Ref. Span: ');text(0.25,.8,num2str(ref_w(wing).b_ref/0.3048));
  
   
text(0.4,.90,'Alpha: '); 	text(.55,.9,num2str(flight_con.alpha*180/pi));
text(0,.75,'Taper: ');      text(0.55,.95,num2str(geometry(wing).T));
text(0.4,.85,'Beta: '); 	text(.55,.85,num2str(flight_con.betha*180/pi));
text(0.4,.8,'Airspeed: ');  text(.55,.8,num2str(flight_con.AS/0.3048));

text(0.65,.9,'P: ');  		text(.8,.9,num2str(flight_con.P));
text(0.65,.85,'Q: '); 		text(.8,.85,num2str(flight_con.Q));
text(0.65,.8,'R: ');  		text(.8,.8,num2str(flight_con.R));
% 
% subplot(2,2,4)
% axis off
text(0,.7,'CL derivatives : ');			

text(0,.65,'CL-alfa');		text(0.15,.65,num2str(iszero(results.CL_a)));
text(0,.6,'CL-beta');		text(0.15,.6,num2str(iszero(results.CL_b)));
text(0,.55,'CL-P');			text(0.15,.55,num2str(iszero(results.CL_P)));
text(0,.5,'CL-Q');			text(0.15,.5,num2str(iszero(results.CL_Q)));
text(0,.45,'CL-R');			text(0.15,.45,num2str(iszero(results.CL_R)));
   
text(0,.35,'Roll derivatives : ');			
   
text(0,.3,'Cl-alfa');		text(0.15,.3,num2str(iszero(results.Cl_a)));
text(0,.25,'Cl-beta');		text(0.15,.25,num2str(iszero(results.Cl_b)));
text(0,.2,'Cl-P');			text(0.15,.2,num2str(iszero(results.Cl_P)));
text(0,.15,'Cl-Q');			text(0.15,.15,num2str(iszero(results.Cl_Q)));
text(0,.1,'Cl-R');			text(0.15,.1,num2str(iszero(results.Cl_R)));
   
text(0.35,.7,'CD derivatives : ');			

text(0.35,.65,'CD-alfa');	text(0.5,.65,num2str(iszero(results.CD_a)));
text(0.35,.6,'CD-beta');	text(0.5,.6,num2str(iszero(results.CD_b)));
text(0.35,.55,'CD-P');		text(0.5,.55,num2str(iszero(results.CD_P)));
text(0.35,.5,'CD-Q');		text(0.5,.5,num2str(iszero(results.CD_Q)));
text(0.35,.45,'CD-R');		text(0.5,.45,num2str(iszero(results.CD_R)));
   
text(0.35,.35,'Pitch derivatives : ');			

text(0.35,.3,'Cm-alfa');	text(.5,.3,num2str(iszero(results.Cm_a)));
text(0.35,.25,'Cm-beta');	text(0.5,.25,num2str(iszero(results.Cm_b)));
text(0.35,.2,'Cm-P');		text(0.5,.2,num2str(iszero(results.Cm_P)));
text(0.35,.15,'Cm-Q');		text(0.5,.15,num2str(iszero(results.Cm_Q)));
text(0.35,.1,'Cm-R');		text(0.5,.1,num2str(iszero(results.Cm_R)));
   
text(0.7,.7,'CY derivatives : ');			

text(0.7,.65,'CY-alfa');	text(0.85,.65,num2str(iszero(results.CY_a)));
text(0.7,.6,'CY-beta');		text(0.85,.6,num2str(iszero(results.CY_b)));
text(0.7,.55,'CY-P');		text(0.85,.55,num2str(iszero(results.CY_P)));
text(0.7,.5,'CY-Q');			text(0.85,.5,num2str(iszero(results.CY_Q)));
text(0.7,.45,'CY-R');		text(0.85,.45,num2str(iszero(results.CY_R)));
   
text(0.7,.35,'Yaw derivatives : ');			

text(0.7,.3,'Cn-alfa');	text(.85,.3,num2str(iszero(results.Cn_a)));
text(0.7,.25,'Cn-beta');	text(0.85,.25,num2str(iszero(results.Cn_b)));
text(0.7,.2,'Cn-P');			text(0.85,.2,num2str(iszero(results.Cn_P)));
text(0.7,.15,'Cn-Q');		text(0.85,.15,num2str(iszero(results.Cn_Q)));
text(0.7,.1,'Cn-R');			text(0.85,.1,num2str(iszero(results.Cn_R)));

% Dervative outputs
results

end
cd ..