Drag methods that are directly specified by analyses. More...

Functions
def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.compressibility_drag_wing.compressibility_drag_wing (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.compressibility_drag_wing_total.compressibility_drag_wing_total (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.induced_drag_aircraft.induced_drag_aircraft (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.miscellaneous_drag_aircraft_ESDU.miscellaneous_drag_aircraft_ESDU (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_fuselage.parasite_drag_fuselage (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_nacelle.parasite_drag_nacelle (state, settings, nacelle)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_pylon.parasite_drag_pylon (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_wing.parasite_drag_wing (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_wing.compute_parasite_drag (re, mac_w, Mc, Tc, xtu, xtl, sweep_w, t_c_w, Sref, Swet, C)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_total.parasite_total (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.spoiler_drag.spoiler_drag (state, settings, geometry)
	spoiler_drag.py More...

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.trim.trim (state, settings, geometry)
	trim.py More...

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.untrimmed.untrimmed (state, settings, geometry)
	untrimmed.py More...

Detailed Description

Drag methods that are directly specified by analyses.

Function Documentation

◆ compressibility_drag_wing()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.compressibility_drag_wing.compressibility_drag_wing	(	state,
		settings,
		geometry
	)

Computes compressibility drag for a wing

Assumptions:
Subsonic to low transonic
Supercritical airfoil

Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)

Inputs:
state.conditions.
  freestream.mach_number                         [Unitless]
  aerodynamics.lift_breakdown.compressible_wings [Unitless]
geometry.thickness_to_chord                      [Unitless]
geometry.sweeps.quarter_chord                    [radians]

Outputs:
total_compressibility_drag                       [Unitless]

Properties Used:
N/A

◆ compressibility_drag_wing_total()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.compressibility_drag_wing_total.compressibility_drag_wing_total	(	state,
		settings,
		geometry
	)

Sums compressibility drag for all wings combined

Assumptions:
None

Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)

Inputs:
state.conditions.aerodynamics.drag_breakdown.compressible[wing.tag].compressibility_drag  [Unitless]
geometry.wings.areas.reference                                                            [m^2]
geometry.reference_area                                                                   [m^2]

Outputs:
total_compressibility_drag                                                                [Unitless]

Properties Used:
N/A

◆ compute_parasite_drag()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_wing.compute_parasite_drag	(	re,
		mac_w,
		Mc,
		Tc,
		xtu,
		xtl,
		sweep_w,
		t_c_w,
		Sref,
		Swet,
		C
	)

Computes the parasite drag due to wings

Assumptions:
Basic fit

Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)

Inputs:
re (Reynolds Number)    [Unitless]
mac_w (Wing MAC)        [m]
Mc (Mach Number)        [Unitless]
Tc (Temperature)        [K]
xtu (Upper Transition)  [Unitless] (percent of chord)
xtl (Lower Transition)  [Unitless] (percent of chord)
sweep_w (Wing Sweep)    [rad]
t_c_w (Wing t/c)        [Unitless]
Sref (Wing Ref Area)    [m^2]
Swet (Wing Wetted Area) [m^2]
C (Form Factor)         [Unitless]
  
Outputs:
(u is upper, l is lower)
wing_parasite_drag                 [Unitless]
k_w    (Form Factor)               [Unitless]
cf_w_u (Skin Friction Coefficient) [Unitless]
cf_w_l                             [Unitless]
k_comp_u (Compressibility Factor)  [Unitless]
k_comp_l                           [Unitless]
k_reyn_u (Reynolds Factor)         [Unitless]
k_reyn_l                           [Unitless]

Properties Used:
N/A

◆ induced_drag_aircraft()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.induced_drag_aircraft.induced_drag_aircraft	(	state,
		settings,
		geometry
	)

Determines induced drag for the full aircraft

Assumptions:
This function operates in one of three ways:
   -An oswald efficiency is provided. All induced drag, inviscid and viscous, is use calculated using that factor
   -A span efficiency is provided. The inviscid induced drag is calculated from that. Viscous induced drag is
        calculated using the viscous_lift_dependent_drag_factor, K, and the parasite drag.
   -The inviscid induced drag from the the lift calculation for each wing, usually a vortex lattice, is used. Viscous induced drag is
        calculated using the viscous_lift_dependent_drag_factor, K, and the parasite drag.
        
    The last two options do not explicitly provide for the case where the fuselage produces an induced drag directly.

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

Inputs:
state.conditions.aerodynamics.
    lift_coefficient                                               [Unitless]
    lift_breakdown.inviscid_wings[wings.*.tag]                     [Unitless]
    drag_breakdown.induced.inviscid                                [Unitless]
    drag_breakdown.induced.inviscid_wings[wings.*.tag]             [Unitless]
    drag_breakdown.parasite[wings.*.tag].parasite_drag_coefficient [Unitless]
    drag_breakdown.parasite[wings.*.tag].reference_area            [m^2]
settings.oswald_efficiency_factor                                  [Unitless]
settings.viscous_lift_dependent_drag_factor                        [Unitless]
settings.span_efficiency                                           [Unitless]


Outputs:
conditions.aerodynamics.drag_breakdown.induced.
     total                                                         [Unitless]
     viscous                                                       [Unitless]
     oswald_efficiency_factor                                      [Unitless]
     viscous_wings_drag                                            [Unitless]

total_induced_drag                                                 [Unitless]


Properties Used:
N/A

◆ miscellaneous_drag_aircraft_ESDU()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.miscellaneous_drag_aircraft_ESDU.miscellaneous_drag_aircraft_ESDU	(	state,
		settings,
		geometry
	)

Computes the miscellaneous drag associated with an aircraft

Assumptions:
Basic fit

Source:
ESDU 94044, figure 1

Inputs:
state.conditions.freestream.mach_number    [Unitless] (actual values not used)
geometry.reference_area                    [m^2]
geometry.wings.areas.wetted                [m^2]
geometry.fuselages.areas.wetted            [m^2]
geometry.network.areas.wetted              [m^2]
geometry.network.number_of_engines         [Unitless]

Outputs:
cd_excrescence (drag)                      [Unitless]

Properties Used:
N/A

◆ parasite_drag_fuselage()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_fuselage.parasite_drag_fuselage	(	state,
		settings,
		geometry
	)

Computes the parasite drag due to the fuselage

Assumptions:
Basic fit

Source:
adg.stanford.edu (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.Common.Fidelity_Zero.Drag.parasite_drag_nacelle.parasite_drag_nacelle	(	state,
		settings,
		nacelle
	)

Computes the parasite drag due to the nacelle

Assumptions:
Basic fit

Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)

Inputs:
state.conditions.freestream.
  mach_number                                [Unitless]
  temperature                                [K]
  reynolds_number                            [Unitless]
nacelle.
  diameter                                   [m]    
  areas.wetted                               [m^2]
  length                                     [m]

Outputs:
propulsor_parasite_drag                      [Unitless]

Properties Used:
N/A

◆ parasite_drag_pylon()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_pylon.parasite_drag_pylon	(	state,
		settings,
		geometry
	)

Computes the parasite drag due to pylons as a proportion of the network drag

Assumptions:
Basic fit

Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)

Inputs:
conditions.aerodynamics.drag_breakdown.parasite[network.tag].
  form_factor                                                   [Unitless]
  compressibility_factor                                        [Unitless]
  skin_friction_coefficient                                     [Unitless]
  wetted_area                                                   [m^2]
  parasite_drag_coefficient                                     [Unitless]
  reynolds_number                                               [Unitless]
geometry.reference_area                                         [m^2]
geometry.nacelle.
  diameter                                                      [m] 

Outputs:
network_parasite_drag                                           [Unitless]

Properties Used:
N/A

◆ parasite_drag_wing()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_drag_wing.parasite_drag_wing	(	state,
		settings,
		geometry
	)

Computes the parasite drag due to wings

Assumptions:
Basic fit

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

Inputs:
settings.wing_parasite_drag_form_factor      [Unitless]
state.conditions.freestream.
  mach_number                                [Unitless]
  temperature                                [K]
  reynolds_number                            [Unitless]
geometry.
  areas.reference                            [m^2]
  chords.mean_aerodynamic                    [m]
  thickness_to_chord                         [Unitless]
  sweeps.quarter_chord                       [radians]
  aspect_ratio                               [Unitless]
  spans.projected                            [m]
  areas.affected                             [m^2]
  areas.wetted                               [m^2]
  transition_x_upper                         [Unitless]
  transition_x_lower                         [Unitless]
  
  
Outputs:
wing_parasite_drag                           [Unitless]

Properties Used:
N/A

◆ parasite_total()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.parasite_total.parasite_total	(	state,
		settings,
		geometry
	)

Sums component parasite drag

Assumptions:
None

Source:
None

Inputs:
geometry.reference_area                             [m^2]
geometry.wings.areas.reference                      [m^2]
geometry.fuselages.areas.front_projected            [m^2] 
geometry.nacelles.diameter                          [m]
conditions.aerodynamics.drag_breakdown.
  parasite[wing.tag].parasite_drag_coefficient      [Unitless]
  parasite[fuselage.tag].parasite_drag_coefficient  [Unitless]
  parasite[nacelle.tag].parasite_drag_coefficient   [Unitless]


Outputs:
total_parasite_drag                                 [Unitless]

Properties Used:
N/A

◆ spoiler_drag()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.spoiler_drag.spoiler_drag	(	state,
		settings,
		geometry
	)

spoiler_drag.py

Created: Jan 2014, A. Variyar Modified: Jan 2016, E. Botero

Adds a spoiler drag increment

Assumptions:
None

Source:
None

Inputs:
settings.spoiler_drag_increment  [Unitless]

Outputs:
spoiler_drag                     [Unitless]

Properties Used:
N/A

◆ trim()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.trim.trim	(	state,
		settings,
		geometry
	)

trim.py

Created: Jan 2014, T. Orra Modified: Jan 2016, E. Botero

Adjusts aircraft drag based on a trim correction

Assumptions:
None

Source:
Unknown

Inputs:
settings.trim_drag_correction_factor                   [Unitless]
state.conditions.aerodynamics.drag_breakdown.untrimmed [Unitless]

Outputs:
aircraft_total_drag_trim_corrected                     [Unitless]

Properties Used:
N/A

◆ untrimmed()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Drag.untrimmed.untrimmed	(	state,
		settings,
		geometry
	)

untrimmed.py