Airplane Aircraft Wing Lift Design Equations Formulas Calculator

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Aircraft Aerospace Aerodynamics Formulas

Problem:

Solve for Lift Force

Inputs:

coefficient of lift (C_L)

unitless

density (p)

velocity (V)

surface area (A)

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Conversions:

coefficient of lift (C_L)

= 0

density (p)

= 0

kilogram/meter^3

velocity (V)

= 0

meter/second

surface area (A)

= 0

meter^2

Solution:

lift force (L) = NOT CALCULATED

Other Units:

Change Equation or Formulas:

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Aircraft and airplane wing lift equations

	Solve for lift force
	Solve for lift coefficient
	Solve for air density
	Solve for velocity
	Solve for lift surface area

Where

L	=	lift force
C_L	=	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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