Functions to perform low-fidelity drag calculations including supersonic.
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.compressibility_drag_total.compressibility_drag_total (state, settings, geometry) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.compressibility_drag_total.lift_wave_drag (conditions, configuration, wing, Sref_main) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.compressibility_drag_total.drag_div (Mc_ii, wing, cl, Sref_main) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.miscellaneous_drag_aircraft.miscellaneous_drag_aircraft (state, settings, geometry) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.parasite_drag_fuselage.parasite_drag_fuselage (state, settings, geometry) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.parasite_drag_nacelle.parasite_drag_nacelle (state, settings, nacelle) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.wave_drag_lift.wave_drag_lift (conditions, configuration, wing) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.wave_drag_volume_raymer.wave_drag_volume_raymer (vehicle, mach, scaling_factor) |
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| def | SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.wave_drag_volume_sears_haack.wave_drag_volume_sears_haack (vehicle, mach, scaling_factor, sears_haack_type=3) |
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Functions to perform low-fidelity drag calculations including supersonic.
◆ compressibility_drag_total()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.compressibility_drag_total.compressibility_drag_total |
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state, |
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settings, |
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geometry |
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Computes compressibility drag for full aircraft including volume drag
Assumptions:
None
Source:
N/A
Inputs:
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
Outputs:
total_compressibility_drag [Unitless]
Properties Used:
N/A
◆ drag_div()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.compressibility_drag_total.drag_div |
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Mc_ii, |
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wing, |
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cl, |
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Sref_main |
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) |
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Use drag divergence mach number to determine drag for subsonic speeds
Assumptions:
Basic fit, subsonic
Source:
http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)
Concorde data can be found in "Supersonic drag reduction technology in the scaled supersonic
experimental airplane project by JAXA" by Kenji Yoshida
Inputs:
wing.
thickness_to_chord [-]
sweeps.quarter_chord [radians]
high_mach [Boolean]
areas.reference [m^2]
Outputs:
cd_c [-]
mcc [-]
MDiv [-]
Properties Used:
N/A
◆ lift_wave_drag()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.compressibility_drag_total.lift_wave_drag |
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conditions, |
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configuration, |
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wing, |
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Sref_main |
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) |
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Determine lift wave drag for supersonic speeds
Assumptions:
Basic fit
Source:
http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)
Inputs:
conditions.freestream.mach_number [-]
configuration (passed to another function)
wing.areas.reference [m^2]
Sref_main [m^2] Main reference area
Outputs:
cd_c_l [-] Wave drag CD due to lift
Properties Used:
N/A
◆ miscellaneous_drag_aircraft()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.miscellaneous_drag_aircraft.miscellaneous_drag_aircraft |
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state, |
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settings, |
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geometry |
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Computes the miscellaneous drag associated with an aircraft
Assumptions:
Basic fit
Source:
http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)
Inputs:
configuration.trim_drag_correction_factor [Unitless]
geometry.nacelle.diameter [m]
geometry.reference_area [m^2]
geometry.wings['main_wing'].aspect_ratio [Unitless]
state.conditions.freestream.mach_number [Unitless] (actual values are not used)
Outputs:
total_miscellaneous_drag [Unitless]
Properties Used:
N/A
◆ parasite_drag_fuselage()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.parasite_drag_fuselage.parasite_drag_fuselage |
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state, |
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settings, |
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geometry |
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Computes the parasite drag due to the fuselage
Assumptions:
Basic fit
Source:
http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)
Inputs:
state.conditions.freestream.
mach_number [Unitless]
temperature [K]
reynolds_number [Unitless]
settings.fuselage_parasite_drag_form_factor [Unitless]
geometry.fuselage.
areas.front_projected [m^2]
areas.wetted [m^2]
lengths.total [m]
effective_diameter [m]
Outputs:
fuselage_parasite_drag [Unitless]
Properties Used:
N/A
◆ parasite_drag_nacelle()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.parasite_drag_nacelle.parasite_drag_nacelle |
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state, |
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settings, |
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nacelle |
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Computes the parasite drag due to the nacelle
Assumptions:
Basic fit
Source:
Raymer equation (pg 283 of Aircraft Design: A Conceptual Approach) (subsonic)
http://aerodesign.stanford.edu/aircraftdesign/drag/BODYFORMFACTOR.HTML (supersonic)
Inputs:
state.conditions.freestream.
mach_number [Unitless]
temperature [K]
reynolds_number [Unitless]
geometry.
nacelle.diameter [m^2]
areas.wetted [m^2]
length [m]
Outputs:
nacelle_parasite_drag [Unitless]
Properties Used:
N/A
◆ wave_drag_lift()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.wave_drag_lift.wave_drag_lift |
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conditions, |
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configuration, |
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wing |
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Computes wave drag due to lift
Assumptions:
Main wing is the primary lift contributor
Source:
Yoshida, Kenji. "Supersonic drag reduction technology in the scaled supersonic
experimental airplane project by JAXA."
Inputs:
conditions.freestream.mach_number [Unitless]
conditions.aerodynamics.lift_coefficient [Unitless]
wing.spans.projected [m]
wing.total_length [m]
wing.aspect_ratio [-]
Outputs:
wave_drag_lift [Unitless]
Properties Used:
N/A
◆ wave_drag_volume_raymer()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.wave_drag_volume_raymer.wave_drag_volume_raymer |
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vehicle, |
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mach, |
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scaling_factor |
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Computes the volume drag
Assumptions:
Basic fit
Source:
D. Raymer, Aircraft Design: A Conceptual Approach, Fifth Ed. pg. 448-449
Inputs:
vehicle.
wings.main_wing.sweeps.leading_edge [rad]
total_length [m]
maximum_cross_sectional_area [m^2]
reference_area [m^2]
Outputs:
vehicle_wave_drag [Unitless]
Properties Used:
N/A
◆ wave_drag_volume_sears_haack()
| def SUAVE.Methods.Aerodynamics.Supersonic_Zero.Drag.wave_drag_volume_sears_haack.wave_drag_volume_sears_haack |
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vehicle, |
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mach, |
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scaling_factor, |
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sears_haack_type = 3 |
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Computes the volume drag
Assumptions:
Basic fit
Source:
Sieron, Thomas R., et al. Procedures and design data for the formulation of aircraft
configurations. WRIGHT LAB WRIGHT-PATTERSON AFB OH, 1993. Page B-3
Inputs:
vehicle.
total_length [m]
maximum_cross_sectional_area [m^2]
reference_area [m^2]
Outputs:
vehicle_wave_drag [Unitless]
Properties Used:
N/A
1.8.15