RCAIDE.Library.Methods.Performance.estimate_stall_speed
estimate_stall_speed#
- estimate_stall_speed(vehicle_mass, reference_area, altitude, maximum_lift_coefficient)[source]#
Calculates the stall speed of an aircraft at a given altitude and maximum lift coefficient.
- Parameters:
vehicle_mass (float) – Total mass of the vehicle [kg]
reference_area (float) – Wing reference area [m²]
altitude (float) – Flight altitude [m]
maximum_lift_coefficient (float) – Maximum lift coefficient of the aircraft [unitless]
- Returns:
V_stall – Stall speed [m/s]
- Return type:
float
Notes
The stall speed is calculated using the standard lift equation solved for velocity:
\[V_{stall} = \sqrt{\frac{2W}{\rho S C_{L_{max}}}}\]- where:
W = mg (vehicle weight)
ρ = air density at altitude
S = reference area
CL_max = maximum lift coefficient
- Major Assumptions
Steady, level flight
Incompressible flow
Standard atmospheric conditions
No wind or atmospheric disturbances
Rigid aircraft structure