Airplane Wing Lift Design Equation Calculator
Aircraft Aerospace Aerodynamics Formulas
Problem:
Solve for Lift Coefficient
Inputs:
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Conversions:
lift force (L)
= 0
= 0
newton
density (p)
= 0
= 0
kilogram/meter^3
velocity (V)
= 0
= 0
meter/second
surface area (A)
= 0
= 0
meter^2
Solution:
lift coefficient (CL) = NOT CALCULATED
Other Units:
Change Equation or Formulas:
Tap or click to solve for a different unknown or equation
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 |
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