Lift Formula
Guys , As we all know the lift formula determines the lift capabilities , So..
L = (1/2) d v2 s CL
* L = Lift, which must equal the airplane's weight in pounds
* d = density of the air. This will change due to altitude.
* v = velocity of an aircraft expressed in feet per second
* s = the wing area of an aircraft in square feet
* CL = Coefficient of lift , which is determined by the type of airfoil and angle of attack.
But can someone explain what does it mean when it says 1/2 the air density , what do you mean by half the density ?? is it half the total value of the air density at an altitude ?
Last edited by Nimer767; 21st Jan 2011 at 10:27.