fastga.models.aerodynamics.external.xfoil.xfoil_polar module

Computation of the airfoil aerodynamic properties using Xfoil.

class fastga.models.aerodynamics.external.xfoil.xfoil_polar.XfoilPolar(**kwargs)

Bases: openmdao.components.external_code_comp.ExternalCodeComp

Runs a polar computation with XFOIL and returns the 2D max lift coefficient.

Intialize the ExternalCodeComp component.

initialize()

Perform any one-time initialization run at instantiation.

setup()

Set up inputs and outputs required for this operation

check_config(logger)

Perform optional error checks.

Parameters

logger (object) – The object that manages logging output.

compute(inputs, outputs)

Function that computes airfoil aerodynamics with XFoil and returns the different 2D aerodynamic parameters.

@param inputs: inputs parameters defined within FAST-OAD-GA @param outputs: outputs parameters defined within FAST-OAD-GA

static fix_multiple_aoa_output_length(alpha, cl, cd, cdp, cm)

Format the size of results that need to be passed as array to the size declared to OpenMDAO if the original array is bigger we resize it, otherwise we complete with zeros. Used when alpha, cl, cd, cdp and cm are arrays. If inside a dataframe use _extract_fix_interpolated_result_length

Parameters

• alpha – angle of attach array

• cl – lift coefficient array

• cd – drag coefficient array

• cdp – pressure drag coefficient array

• cm – moment coefficient array

Returns

the input array with the proper size for OpenMDAO