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

compute_horizontal_tail_weight#

compute_horizontal_tail_weight(vehicle, wing)[source]#

Computes the horizontal 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 horizontal tail instance containing:
    • areas.referencefloat

      Planform area [m²]

    • taperfloat

      Taper ratio

Returns:

WHT – Horizontal 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

  • All-moving or fixed stabilizer with elevator

  • Standard aluminum construction

  • Conventional aerodynamic loads

  • No special design features (e.g., folding)

Theory Weight is computed using: .. math:

W_{HT} = 0.53 S_{HT} (TOGW)^{0.2} (\lambda_{HT} + 0.5)
where:
  • S_HT = horizontal tail area

  • TOGW = takeoff gross weight

  • λ_HT = horizontal tail taper ratio

The correlation accounts for:
  • Bending and torsional stiffness requirements

  • Control surface integration

  • Attachment structure

  • Standard design margins

References

[1] NASA Langley Research Center, “Flight Optimization System, Release 8.23,

User’s Guide”, 2011.