Functions that are needed by aerodynamics methods. More...

Functions
def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.asymmetry_drag.asymmetry_drag (state, geometry, windmilling_drag_coefficient=0.)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.compressible_mixed_flat_plate.compressible_mixed_flat_plate (Re, Ma, Tc, xt)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.compressible_turbulent_flat_plate.compressible_turbulent_flat_plate (Re, Ma, Tc)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.estimate_2ndseg_lift_drag_ratio.estimate_2ndseg_lift_drag_ratio (state, settings, geometry)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.wave_drag_lift.wave_drag_lift (conditions, configuration, wing)

def	SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.windmilling_drag.windmilling_drag (geometry, state)

Detailed Description

Functions that are needed by aerodynamics methods.

Function Documentation

◆ asymmetry_drag()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.asymmetry_drag.asymmetry_drag	(	state,
		geometry,
		windmilling_drag_coefficient = `0.`
	)

Computes asymmetry drag due to engine failure

Assumptions:
Two engine aircraft

Source:
Unknown source

Inputs:
state.conditions.freestream.dynamic_pressure                                                [Pa]
state.conditions.aerodynamics.drag_breakdown.windmilling_drag.windmilling_drag_coefficient  [Unitless]
geometry.
  mass_properties.center_of_gravity                                                         [m]
  networks. 
    number_of_engines                                                                       [Unitless]
  wings.
    tag                                                                                     
    sref (this function probably doesn't run)                                               [m^2]
spans.projected                                                                         [m]
  reference_area                                                                            [m^2]

Outputs:
asymm_trim_drag_coefficient                                                                 [Unitless]
(packed in state.conditions.aerodynamics.drag_breakdown.asymmetry_trim_coefficient)

Properties Used:
N/A

◆ compressible_mixed_flat_plate()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.compressible_mixed_flat_plate.compressible_mixed_flat_plate	(	Re,
		Ma,
		Tc,
		xt
	)

Computes the coefficient of friction for a flat plate given the 
input parameters. Also returns the correction terms used in the
computation.

Assumptions:
Reynolds number between 10e5 and 10e9
xt between 0 and 1

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

Inputs:
Re (Reynolds number)                                             [Unitless]
Ma (Mach number)                                                 [Unitless]
Tc (temperature)                                                 [K]
xt (turbulent transition point as a proportion of chord length)  [Unitless]

Outputs:
cf_comp (coefficient of friction)                                [Unitless]
k_comp (compressibility correction)                              [Unitless]
k_reyn (Reynolds number correction)                              [Unitless]

Properties Used:
N/A

◆ compressible_turbulent_flat_plate()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.compressible_turbulent_flat_plate.compressible_turbulent_flat_plate	(	Re,
		Ma,
		Tc
	)

Computes the coefficient of friction for a flat plate given the 
input parameters. Also returns the correction terms used in the
computation.

Assumptions:
Reynolds number between 10e5 and 10e9
Fully turbulent

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

Inputs:
Re (Reynolds number)                                             [Unitless]
Ma (Mach number)                                                 [Unitless]
Tc (temperature)                                                 [K]

Outputs:
cf_comp (coefficient of friction)                                [Unitless]
k_comp (compressibility correction)                              [Unitless]
k_reyn (Reynolds number correction)                              [Unitless]

Properties Used:
N/A

◆ estimate_2ndseg_lift_drag_ratio()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.estimate_2ndseg_lift_drag_ratio.estimate_2ndseg_lift_drag_ratio	(	state,
		settings,
		geometry
	)

Estimates the 2nd segment climb lift to drag ratio (all engine operating)

Assumptions:
All engines operating

Source:
Fig. 27.34 of "Aerodynamic Design of Transport Airplane" - Obert

Inputs:
config.
  V2_VS_ratio              [Unitless]
  wings.
    areas.reference        [m^2]
spans.projected        [m]
aspect_ratio           [Unitless]
  maximum_lift_coefficient [Unitless]

Outputs:
lift_drag_ratio            [Unitless]

Properties Used:
N/A

◆ wave_drag_lift()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.wave_drag_lift.wave_drag_lift	(	conditions,
		configuration,
		wing
	)

Computes wave drag due to lift

Assumptions:
Simplified equations

Source:
http://adg.stanford.edu/aa241/drag/ssdragcalc.html

Inputs:
conditions.freestream.mach_number        [Unitless]
conditions.aerodynamics.lift_coefficient [Unitless]
wing.total_length                        [m]
wing.areas.reference                     [m^2]

Outputs:
wave_drag_lift                           [Unitless]

Properties Used:
N/A

◆ windmilling_drag()

def SUAVE.Methods.Aerodynamics.Common.Fidelity_Zero.Helper_Functions.windmilling_drag.windmilling_drag	(	geometry,
		state
	)

Computes windmilling drag for turbofan engines

Assumptions:
None

Source:
http://www.dept.aoe.vt.edu/~mason/Mason_f/AskinThesis2002_13.pdf

Inputs:
geometry.
  max_mach_operational        [Unitless]
  reference_area              [m^2]
  wings.sref                  [m^2]
  networks.
    areas.wetted              [m^2]
    length                    [m]

Outputs:
windmilling_drag_coefficient  [Unitless]

Properties Used:
N/A