SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line Class Reference

Inheritance diagram for SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line:

Public Member Functions
def	__defaults__ (self)
def	initialize (self, use_surrogate, n_sw, n_cw, propeller_wake_model, mf, mn, dcs)
def	evaluate (self, state, settings, geometry)
def	sample_training (self)
def	build_surrogate (self)
Public Member Functions inherited from SUAVE.Analyses.Aerodynamics.Aerodynamics.Aerodynamics
def	evaluate (self, state)
def	finalize (self)
Public Member Functions inherited from SUAVE.Analyses.Analysis.Analysis
def	compile (self, *args, **kwarg)
def	initialize (self, *args, **kwarg)
def	evaluate (self, *args, **kwarg)
def	finalize (self, *args, **kwarg)
def	__call__ (self, *args, **kwarg)

Public Attributes
	tag
	geometry
	settings
	training
	surrogates
Public Attributes inherited from SUAVE.Analyses.Aerodynamics.Aerodynamics.Aerodynamics
	tag
	geometry
	settings
Public Attributes inherited from SUAVE.Analyses.Analysis.Analysis
	tag
	features
	settings

Detailed Description

This builds a surrogate and computes lift using a basic lifting line.

Assumptions:
None

Source:
None

Member Function Documentation

__defaults__()

def SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line.__defaults__

(

self

)

This sets the default values and methods for the analysis.

Assumptions:
None

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
N/A

Reimplemented from SUAVE.Analyses.Aerodynamics.Aerodynamics.Aerodynamics.

build_surrogate()

def SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line.build_surrogate

(

self

)

Build a surrogate using sample evaluation results.

Assumptions:
None

Source:
N/A

Inputs:
see properties used

Outputs:
self.surrogates.
  lift_coefficient       <np.poly1d>
  wing_lift_coefficients <np.poly1d> (multiple surrogates)

Properties Used:
self.
  training.
    angle_of_attack        [radians]
    lift_coefficient       [-]
    wing_lift_coefficients [-] (wing specific)
    drag_coefficient       [-]
    wing_drag_coefficients [-] (wing specific)

evaluate()

def SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line.evaluate	(		self,
			state,
			settings,
			geometry
	)

Evaluates lift and drag using available surrogates.

Assumptions:
None

Source:
N/A

Inputs:
state.conditions.
  freestream.dynamics_pressure       [-]
  angle_of_attack                    [radians]

Outputs:
conditions.aerodynamics.lift_breakdown.
  inviscid_wings[wings.*.tag]        [-] CL (wing specific)
  inviscid_wings.total               [-] CL
conditions.aerodynamics.drag_breakdown.induced
  inviscid_wings[wings.*.tag]        [-] CDi (wing specific)
  total                              [-] CDi
  inviscid                           [-] CDi

conditions.aerodynamics.
  inviscid_wings_lift                [-] CL

Properties Used:
self.surrogates.
  lift_coefficient                   [-] CL
  wing_lift_coefficient[wings.*.tag] [-] CL (wing specific)
  drag_coefficient                   [-] CDi
  wing_drag_coefficient[wings.*.tag] [-] CDi (wing specific)

initialize()

def SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line.initialize	(		self,
			use_surrogate,
			n_sw,
			n_cw,
			propeller_wake_model,
			mf,
			mn,
			dcs
	)

Drives functions to get training samples and build a surrogate.

Assumptions:
None

Source:
N/A

Inputs:
None

Outputs:
None

Properties Used:
None

sample_training()

def SUAVE.Analyses.Aerodynamics.Lifting_Line.Lifting_Line.sample_training

(

self

)

Call methods to run vortex lattice for sample point evaluation.

Assumptions:
None

Source:
N/A

Inputs:
see properties used

Outputs:
self.training.
  lift_coefficient            [-] 
  wing_lift_coefficients      [-] (wing specific)

Properties Used:
self.geometry.wings.*.tag
self.settings                 (passed to calculate vortex lattice)
self.training.angle_of_attack [radians]

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The documentation for this class was generated from the following file:

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Analyses/Aerodynamics/Lifting_Line.py