RCAIDE.Library.Methods.Aerodynamics.Common.Drag.parasite_drag_fuselage
parasite_drag_fuselage#
- parasite_drag_fuselage(state, settings, fuselage)[source]#
Computes the parasite drag due the a fuselage (or boom)
- Assumptions:
None
- Source:
Stanford AA241 A/B Course Notes
- Parameters:
state.conditions.freestream. – mach_number (numpy.ndarray): mach_number [Unitless] temperature (numpy.ndarray): temperature [K] reynolds_number (numpy.ndarray): Reynolds number [Unitless]
settings.fuselage_parasite_drag_form_factor (numpy.ndarray) – form factor [Unitless]
geometry.fuselage. – areas.front_projected (float): projected front area [m^2] areas.wetted (float): wetted area [m^2] lengths.total (float): length [m] effective_diameter (float): effective diamater [m]
- Returns:
None