OpenVSP_Wave_Drag

Functions to perform wave drag calculations using OpenVSP. More...

Functions
def	SUAVE.Methods.Aerodynamics.OpenVSP_Wave_Drag.compressibility_drag_total.compressibility_drag_total (state, settings, geometry)
def	SUAVE.Methods.Aerodynamics.OpenVSP_Wave_Drag.compressibility_drag_total.lift_wave_drag (conditions, configuration, wing, k, Sref_main, flag105)
def	SUAVE.Methods.Aerodynamics.OpenVSP_Wave_Drag.wave_drag_volume.wave_drag_volume (conditions, geometry, flag105, num_slices=20, num_rots=10)

Detailed Description

Functions to perform wave drag calculations using OpenVSP.

Function Documentation

compressibility_drag_total()

def SUAVE.Methods.Aerodynamics.OpenVSP_Wave_Drag.compressibility_drag_total.compressibility_drag_total	(		state,
			settings,
			geometry
	)

Computes compressibility drag for full aircraft including volume drag through OpenVSP

Assumptions:
None

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

Inputs:
settings.number_slices
settings.number_rotations
state.conditions.aerodynamics.
  lift_breakdown.compressible_wings      [-]
state.conditions.freestream.mach_number  [-]
geometry.wings.*.tag                       

Outputs:
drag_breakdown.compressible[wing.tag].
  divergence_mach                        [-]
drag_breakdown.compressible.total        [-]                    
drag_breakdown.compressible.total_volume [-]
drag_breakdown.compressible.total_lift   [-]
cd_c                                     [-] Total compressibility drag

Properties Used:
N/A

lift_wave_drag()

def SUAVE.Methods.Aerodynamics.OpenVSP_Wave_Drag.compressibility_drag_total.lift_wave_drag	(		conditions,
			configuration,
			wing,
			k,
			Sref_main,
			flag105
	)

Determine lift wave drag for supersonic speeds

Assumptions:
Basic fit

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

Inputs:
conditions.freestream.mach_number [-]
configuration                     (passed to another function)
wing.areas.reference              [m^2]
k                                 (unused)
Sref_main                         [m^2] Main reference area
flag105                           <boolean> Check if calcs are for Mach 1.05

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

Properties Used:
N/A

wave_drag_volume()

def SUAVE.Methods.Aerodynamics.OpenVSP_Wave_Drag.wave_drag_volume.wave_drag_volume	(		conditions,
			geometry,
			flag105,
			num_slices = 20,
			num_rots = 10
	)

Determine volume wave drag for supersonic speeds using OpenVSP

Assumptions:
None

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

Inputs:
conditions.
  freestream.mach_number [-]
geometry.
  reference_area         [m^2]
  tag                    <string>
flag105                  <boolean> determines is Mach = 1.05 is used
num_slices               [-] Slices used by OpenVSP (optional - defaults to 20)
num_rots                 [-] Rotations used by OpenVSP (optional - defaults to 10)

Outputs:
cd_w_all

Properties Used:
N/A