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

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.

Was this page helpful? Share it.
submit to reddit

Popular Pages:


Site Links:

Web Apps, Rich Internet Application, Technical Tools, Specifications, How to Guides, Training, Applications, Examples, Tutorials, Reviews, Answers, Test Review Resources, Analysis, Homework Solutions, Help, Data and Information for Engineers, Technicians, Teachers, Tutors, Researchers, K-12 Education, College and High School Students, Science Fair Projects and Scientists

By Jimmy Raymond
View Jimmy Rayamond's profile on LinkedIn

Contact: aj@ajdesigner.com

Privacy Policy, Disclaimer and Terms

Copyright 2002-2015