The CL should be a 1×87 matrix but only comes out to one answer. Thank you for your help!
GrossWeight=207357; %lbs%
%wing span in feet%
b=108; %wing area ft^2%
S=1700; AR=6.86; e=0.77; %wing height above ground in feet%
Wh=8.2; TAperengine=16000;%lb%
SFC=0.62; Nengines=3; ParCD=0.018; Wf=54124;%fuel weight in lbs%
ro30000=0.000891; dv=10; Vinf=0:dv:860;%ft/s%
GW=ones(1,length(Vinf))*GrossWeight; CL=GW/(0.5*ro30000*(Vinf.^2)*S);
Best Answer