Airplane Wing Lift Design Equation Calculator

Aircraft Aerospace Aerodynamics Formulas


Solving For Lift Force
Lift Force

Inputs:

coefficient of lift (CL)
density (p)
velocity (V)
surface area (A)


Conversions:

coefficient of lift (CL)
= 0
= 0
density (p)
= 0
= 0
kilogram/meter^3
velocity (V)
= 0
= 0
meter/second
surface area (A)
= 0
= 0
meter^2

Solution:

lift force (L)
= NOT CALCULATED

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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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