PPRuNe Forums - View Single Post

18th February 2012 | 15:37

#3 (permalink)

tuaapache

Joined: Apr 2010

Posts: 96

Likes: 0

From: Bangkok

Thanks for the advice. If I remember correctly, the lift formula is 1/2*AirDensity*CoeffientOfLift*V^2*Surface of the wing?

Reply