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 | |
This builds a surrogate and computes lift using a basic lifting line. Assumptions: None Source: None
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.
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)
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)
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
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]