RCAIDE.Library.Methods.Performance.find_take_off_weight_given_tofl

find_take_off_weight_given_tofl

find_take_off_weight_given_tofl(vehicle, analyses, target_tofl, altitude=0, delta_isa=0)

Estimates the maximum allowable takeoff weight for a given takeoff field length requirement.

Parameters:

• vehicle (Vehicle) –

  The vehicle instance containing:

  • mass_properties.operating_emptyfloat

    Operating empty weight [kg]

  • mass_properties.max_takeofffloat

    Maximum takeoff weight [kg]

• analyses (Analyses) – Container with atmosphere and aerodynamic analyses

• target_tofl (float or ndarray) – Target takeoff field length(s) [m]

• altitude (float, optional) – Airport altitude [m], default 0

• delta_isa (float, optional) – Temperature offset from ISA conditions [K], default 0

Returns:

max_tow – Maximum allowable takeoff weight(s) for given field length(s) [kg]

Return type:

ndarray

Notes

Uses an interpolation approach by:

1. Creating array of possible takeoff weights between OEW and 110% MTOW

2. Computing TOFL for each weight

3. Interpolating to find weight that gives target TOFL

Major Assumptions

• Linear interpolation between computed points is valid

• Target TOFL is within achievable range

• Meets assumptions from estimate_take_off_field_length

Theory Takeoff field length varies approximately with W/T where:

• W = aircraft weight

• T = available thrust

\[TOFL \propto \frac{W}{T}\]

See also

RCAIDE.Library.Methods.Performance.estimate_take_off_field_length