Lift-to-Drag Ratio Calculator

Property to Calculate:

Lift force (L) or Lift Coefficient (C_L):

Drag force (D) or Drag Coefficient (C_D):

How This Is Calculated

$$ \frac{L}{D} = \frac{C_L}{C_D} $$ where:

L = Lift force (N)

D = Drag force (N)

C_L = Lift coefficient (Dimensionless)

C_D = Drag coefficient (Dimensionless)

Assumptions

Aircraft is in steady-state flow conditions.
Flow is incompressible.
Lift and drag remain constant.
The relationship between lift and drag coefficients is linear.
Ground effects are neglected.

Related Calculators

Lift

Drag

Rate of Climb

Stall Speed

Turn Radius