Airplane Wing Lift Design Equation Calculator

Aircraft Aerospace Aerodynamics Formulas

Solving For Air Density

Inputs:

 lift force (L) newtondynegram forcekilogram-meter/second^2kilogram forcekippound forcepoundal
 lift coefficient (CL)
 velocity (V) meter/secondcentimeter/hourcentimeter/secondfoot/dayfoot/hourfoot/minutefoot/secondinch/dayinch/hourinch/minuteinch/secondkilometer/daykilometer/hourkilometer/minutekilometer/secondknotmach sea level 15 Cmeter/daymeter/hourmeter/minutemile/daymile/hourmile/minutemile/secondmillimeter/secondspeed of light in vacuumyard/second
 surface area (A) meter^2acre internationalacre US surveyarebarncentimeter^2foot^2hectareinch^2kilometer^2mile^2micrometer^2millimeter^2mile^2 nauticalnanometer^2pingtownshipyard^2

Conversions:

 lift force (L)= 0 = 0newton
 lift coefficient (CL)= 0 = 0
 velocity (V)= 0 = 0meter/second
 surface area (A)= 0 = 0meter^2

Solution:

 air density (p)= NOT CALCULATED

Other Units:

Change Equation
Select to solve for a different unknown
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 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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By Jimmy Raymond

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