I am trying to plot

dan
2018 4 2
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更新时间：2018 4 2
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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);

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 采纳的回答

Star Strider
Star Strider 2018-4-2

1 个投票

You need to vectorizse the division in the ‘CL’ calculation:
CL=GW ./ (0.5*ro30000*(Vinf.^2)*S);
↑ ← VECTORISE HERE

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