The formula for lift is the following: L = (1/2) D v2 s CL D is the density of the air where the plane is flying. This varies with the altitude. The higher the altitude, the less dense the air, the more lift required. We will use a chart for this value. v is the velocity of the plane in feet per second. s is the wing area in square feet. CL is called the coefficient of lift. The lift coefficient is a number that characterizes different parameters of a wing, including its curvature, thickness, and angle of attack. The value of CL is determined by wind tunnel testing.

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Please send any comments to:
Curator: Tom.Benson@grc.nasa.gov
Responsible Official: Kathy.Zona@grc.nasa.gov