clc

mincl = 1.6;
maxcd = 0.02;

[raitomax m1]=sort(clcdmax300(:,1),'descend');
maxratio3 = [m1 clcdmax300(m1,:)];

max_parsed = maxratio3(maxratio3(:,3)>mincl & maxratio3(:,4)<maxcd,:);

[m n]=sort(max_parsed(:,2),'descend');
sortmax_parsed = max_parsed(n,:);


% [clmax m2]=sort(clcdmax300(:,2),'descend');
% maxcl3 = clcdmax300(m2(1:20),:)
% [cdmin m3]=sort(clcdmax300(:,3));
% mincd3 = clcdmax300(m3(1:20),:)

disp('Re=300k Arranged by Cl/Cd_max - greatest to least')
for bf=1:6
    tfoil = foil300(sortmax_parsed(bf,1))
    
    figure(1)
    subplot(2,3,bf)
    plot(tfoil.c_d,tfoil.c_l,'r')
    xlabel('C_d')
    ylabel('C_l')
    axis([0 .06 -.2 2])
    title(['C_l vs. C_d - ',tfoil.filename(1:length(tfoil.filename)-6)])
    
    figure(2)
    subplot(2,3,bf)
    plot(tfoil.aoa,tfoil.c_l,'b')
    hold on
    plot(tfoil.aoa,tfoil.c_d,'k')
    xlabel('AoA')
    axis([-15 40 -.5 2.5])
    title(['C_l/C_d vs. AoA - ',tfoil.filename(1:length(tfoil.filename)-6)])
%    legend('C_l','C_d')
    hold off
    
    figure(3)
    subplot(2,3,bf)
    [xt yt] = airfoil_geo(['airfoils/',tfoil.filename(1:length(tfoil.filename)-6),'.dat']);
    plot(xt,yt,'b')
    xlabel('chord')
    axis equal
    title(['Airfoil Shape - ',tfoil.filename(1:length(tfoil.filename)-6)])
    
    clear tfoil
end