Stall Speed Calculator

Stall speed (v_stall):

Aircraft weight (W):

Air density (ρ):

Wing area (S):

Coefficient of lift (C_L):

How This Is Calculated

$$ v_{stall} = \sqrt{\frac{2W}{\rho S C_L}} $$ where:

v_stall = Stall speed (m²/s)

W = Aircraft weight (kg)

ρ = Air density (kg/m³)

S = Wing area (m²)

C_L = Coefficient of lift (Dimensionless)

Assumptions

The aircraft is in steady, level flight at the point of stall.
The lift coefficient remains constant.
Air density is uniform.
There is no wind or other external effects.
The wing area is fixed.

Related Calculators

Lift

Drag

Lift-to-Drag Ratio

Turn Radius

Turn Rate