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Airplane Wing Lift Design Equation Calculator

Aircraft Aerospace Aerodynamics Formulas
Solving For Lift Coefficient
Lift Coefficient

Inputs:

lift force (L)
density (p)
velocity (V)
surface area (A)
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Conversions:

lift force (L)
= 0
= 0
newton
density (p)
= 0
= 0
kilogram/meter^3
velocity (V)
= 0
= 0
meter/second
surface area (A)
= 0
= 0
meter^2

Solution:

lift coefficient (CL)
= NOT CALCULATED

Other Units:

Change Equation
Select to solve for a different unknown
Aircraft and airplane wing lift equations
lift forceSolve for lift force
lift coefficientSolve for lift coefficient
air densitySolve for air density
velocitySolve for velocity
lift surface areaSolve for lift surface area
Where
L=lift force
CL=lift coefficient
p=air density
V=velocity
A=lift surface area
Reference - Books:
1) Munson, B.R., D. F. Young, and T. H. Okiishi. 1994. Fundamentals of Fluid Mechanics. John Wiley and Sons, Inc. 2nd ed.
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