I am trying to plot

The CL should be a 1x87 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);

Answer 1

[Star Strider]

You need to vectorizse the division in the ‘CL’ calculation:

CL=GW ./ (0.5*ro30000*(Vinf.^2)*S);
      ↑ ←  VECTORISE HERE