RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.BWB.FLOPS.compute_aft_centerbody_weight
compute_aft_centerbody_weight#
- compute_aft_centerbody_weight(no_of_engines, aft_centerbody_area, aft_centerbody_taper, TOGW)[source]#
Computes the structural weight of the aft section of a BWB centerbody using regression-based methods.
- Parameters:
no_of_engines (int) – Number of engines mounted on aft centerbody
aft_centerbody_area (float) – Planform area of aft centerbody section [m²] Typically measured behind 70% chord
aft_centerbody_taper (float) – Taper ratio of aft centerbody section Excludes chord taken up by pressurized cabin
TOGW (float) – Takeoff gross weight of aircraft [kg]
- Returns:
W_aft – Estimated structural weight of BWB aft centerbody [kg]
- Return type:
float
Notes
Uses regression equations derived from FEA studies to estimate the structural weight required to handle engine loads and aerodynamic forces.
- Major Assumptions
Engines are mounted on the aft centerbody
Aft section is unpressurized
Linear relationship with planform area
Engine count affects weight through simple scaling
Structure sized primarily by engine and aerodynamic loads
Theory Weight is computed using: .. math:
W_{aft} = (1 + 0.05n_e)\cdot 0.53\cdot S_{aft}\cdot W^{0.2}\cdot(\lambda + 0.5)
- where:
n_e = number of engines
S_aft = aft centerbody area
W = takeoff weight
λ = taper ratio
References
- [1] Bradley, K. R., “A Sizing Methodology for the Conceptual Design of
Blended-Wing-Body Transports,” NASA/CR-2004-213016, 2004.