L is the amount of Lift produced, ρ {\displaystyle \rho } is the air density, V is the true airspeed of the airplane or the Velocity of the airplane, relative to the air S is the area of the wing C L {\displaystyle C_{L}} is the lift coefficient, which is determined by the shape of the airfoil used and the angle at which the wing meets the air (or angle of attack).