is the formula below valid to calculate the lift coefficient for a delta wing?(adsbygoogle = window.adsbygoogle || []).push({});

Cl=2*L/(rho*v^2*A)

L=lift (N)

rho= air density

v= air velocity

A=wing area

im doing a subsonic wind tunnel project where im going to measure the lift for a low aspect ratio delta wing. should i use another theory to calculate the lift?

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# How to calculate lift for delta wing

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