RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.Transport.FLOPS.compute_vertical_tail_weight

compute_vertical_tail_weight#

compute_vertical_tail_weight(vehicle, wing)[source]#

Computes the vertical tail weight using NASA FLOPS weight estimation method.

Parameters:

  • vehicle (Vehicle) –

    The vehicle instance containing:
    • mass_properties.max_takeofffloat

      Maximum takeoff weight [kg]

  • wing (Wing) –

    The vertical tail instance containing:
    • taperfloat

      Taper ratio

    • areas.referencefloat

      Planform area [m²]

Returns:

WVT – Vertical tail weight [kg]

Return type:

float

Notes

Uses FLOPS correlation developed from transport aircraft database. The method accounts for tail size, aircraft weight, and planform effects.

Major Assumptions

  • Conventional tail configuration

  • Single vertical tail (NVERT = 1). Multiple vertical tails are computed separately and summed.

Theory Weight is computed using: .. math:

W_{VT} = 0.32W_{TO}^{0.3}(\lambda_{VT} + 0.5)N_{VT}^{0.7}S_{VT}^{0.85}
where:

  • W_TO = takeoff gross weight

  • λ_VT = vertical tail taper ratio

  • N_VT = number of vertical tails (fixed at 1)

  • S_VT = vertical tail area

The correlation accounts for:

  • Bending and torsional stiffness requirements

  • Rudder integration

  • Attachment structure

  • Standard design margins

  • Directional stability requirements

References

[1] NASA Flight Optimization System (FLOPS)

See also

RCAIDE.Library.Methods.Weights.Correlation_Buildups.FLOPS.compute_horizontal_tail_weight