RCAIDE.Library.Methods.Aerodynamics.Common.Drag.compressibility_drag

compressibility_drag

compressibility_drag(state, settings, geometry)

Computes compressibility drag for full aircraft including volume drag

Assumptions: None

Source: None

Args: settings.

begin_drag_rise_mach_number [Unitless] end_drag_rise_mach_number [Unitless] peak_mach_number [Unitless] transonic_drag_multiplier [Unitless] volume_wave_drag_scaling [Unitless]

state.conditions.aerodynamics.lift_breakdown.compressible_wings [Unitless] state.conditions.freestream.mach_number [Unitless] geometry.maximum_cross_sectional_area [m^2] (used in subfunctions) geometry.total_length [m] (used in subfunctions) geometry.reference_area [m^2] geometry.wings

Returns: total_compressibility_drag [Unitless]

Properties Used: None

transonic_drag_function(Mach, a_vertex, peak_mach, peak_volume_total)

parabolic approximation of drag rise in the transonic region

Assumptions: Basic fit

Source: None

Args: Mach a_vertex peak_mach peak_volume_total

Returns: transonic_drag

lift_wave_drag(conditions, configuration, geometry)

Determine lift wave drag for supersonic speeds

Assumptions: Basic fit

Source: http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)

Args: conditions.freestream.mach_number [-] configuration (passed to another function) wing.areas.reference [m^2] Sref_main [m^2] Main reference area

Returns: cd_c_l [-] Wave drag CD due to lift