# Airplane Wing Lift Design Equation Calculator

## Aircraft Aerospace Aerodynamics Formulas

Solving For Velocity

#### Inputs:

 lift force (L) newtondynegram forcekilogram-meter/second^2kilogram forcekippound forcepoundal
 lift coefficient (CL)
 density (p) kilogram/meter^3gram/centimeter^3gram/meter^3gram/milliliterkilogram/deciliterkilogram/litermilligram/literounce/foot^3ounce/inch^3pound/foot^3pound/bushel UKpound/bushel USpound/gallon UKpound/gallon USpound/inch^3pound/yard^3ton metric/meter^3slug/foot^3slug/inch^3
 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
 density (p)= 0 = 0kilogram/meter^3
 area (A)= 0 = 0meter^2

#### Solution:

 velocity (V)= 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

Contact: aj@ajdesigner.com