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:
- 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.