Stall Speed Calculator
SI
Imp
Imperial
Inputs
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Aircraft weight
(W)
Loaded aircraft mass/weight for the stall-speed estimate.
lb
Wing area
(S)
Planform wing area.
ft²
Air density
(rho)
Use local density if known; standard sea-level density is 1.225 kg/m3.
lb/ft³
Maximum lift coefficient
(CLmax)
Results
Default result
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Estimated stall speed
(Vs)
51.0
kt
Pass
Also computed
Wing loading
13.2
lb/ft²
Dynamic pressure at stall
421
Pa
Method notes
2 notes
Uses Vs = sqrt(2W / (rho * S * CLmax)) with W = mass * g.
Actual stall speeds depend on configuration, CG, propwash, contamination, position error and the approved flight manual.
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