RCAIDE.Library.Methods.Performance.estimate_take_off_field_length

estimate_take_off_field_length#

estimate_take_off_field_length(vehicle, analyses, altitude=0, delta_isa=0, compute_2nd_seg_climb=False)[source]#

Computes the takeoff field length and optionally the second segment climb gradient for a given vehicle configuration.

Parameters:

vehicle (Vehicle) –
The vehicle instance containing:
- mass_properties.takeofffloat
  Takeoff weight [kg]
- reference_areafloat
  Wing reference area [m²]
- V2_VS_ratiofloat, optional
  Ratio of V2 to stall speed, default 1.20
- networks.*.number_of_enginesint
  Number of engines per network
analyses (Analyses) – Container with atmosphere and aerodynamic analyses
altitude (float, optional) – Airport altitude [m], default 0
delta_isa (float, optional) – Temperature offset from ISA conditions [K], default 0
compute_2nd_seg_climb (bool, optional) – Flag to compute second segment climb gradient, default False

Returns:

takeoff_field_length (float) – Required takeoff field length [m]
second_seg_climb_gradient (float, optional) – Second segment climb gradient [unitless], only if compute_2nd_seg_climb=True

Notes

The takeoff field length is computed using empirical correlations: .. math:

TOFL = k_0 + k_1(V_2^2/T/W) + k_2(V_2^2/T/W)^2

where k₀, k₁, k₂ depend on number of engines:

Major Assumptions

Sea level standard conditions unless specified
Standard V2 speed ratio (1.20 × stall speed)
No wind conditions
Dry runway surface
For second segment climb:
- One engine inoperative
- Only validated for two-engine aircraft

Theory Second segment climb gradient is computed as:

\[\gamma = T/W - 1/L/D\]

where L/D includes effects of:

References

[1] Stanford University AA241 Aircraft Design Course Notes http://adg.stanford.edu/aa241/AircraftDesign.html