ibl.reference.XFoilReader

class ibl.reference.XFoilReader(filename='')

Bases: object

XFoil dump file reader.

This class is an interface to the dump file from XFoil. The data for the airfoil and wake are read in and processed into upper flow and lower flow at the stagnation point (not leading edge) and the wake. Each portion is stored separately and the parameters are obtained separately.

Parameters:: filename (str)

__init__(filename='')

Initialize class with filename.

Parameters:: filename (str, optional) – Name of XFoil dump file to parse, by default “”
Return type:: None

Methods

`__init__`([filename])	Initialize class with filename.
`c_f_lower`()	Return the skin friction coefficient for lower surface of airfoil.
`c_f_upper`()	Return the skin friction coefficient for upper surface of airfoil.
`delta_d_lower`()	Return the displacement thicknesses for lower surface of airfoil.
`delta_d_upper`()	Return the displacement thicknesses for upper surface of airfoil.
`delta_d_wake`()	Return the displacement thicknesses for airfoil wake.
`delta_k_lower`()	Return the kinetic energy thicknesses for lower surface of airfoil.
`delta_k_upper`()	Return the kinetic energy thicknesses for upper surface of airfoil.
`delta_m_lower`()	Return the momentum thicknesses for lower surface of airfoil.
`delta_m_upper`()	Return the momentum thicknesses for upper surface of airfoil.
`delta_m_wake`()	Return the momentum thicknesses for airfoil wake.
`ke_defect_lower`()	Return the kinetic energy defect for lower surface of airfoil.
`ke_defect_upper`()	Return the kinetic energy defect for upper surface of airfoil.
`lower`(i)	Return the specified data on the lower surface of airfoil.
`lower_count`()	Return number of points on the lower surface of airofil.
`mass_defect_lower`()	Return the mass defect for lower surface of airfoil.
`mass_defect_upper`()	Return the mass defect for upper surface of airfoil.
`mom_defect_lower`()	Return the momentum defect for lower surface of airfoil.
`mom_defect_upper`()	Return the momentum defect for upper surface of airfoil.
`s_lower`()	Return arc-length distances from stagnation point for lower surface.
`s_upper`()	Return arc-length distances from stagnation point for upper surface.
`s_wake`()	Return arc-length distances from airfoil trailing edge.
`shape_d_lower`()	Return the displacement shape factor for lower surface of airfoil.
`shape_d_upper`()	Return the displacement shape factor for upper surface of airfoil.
`shape_d_wake`()	Return the displacement shape factor for airfoil wake.
`shape_k_lower`()	Return the kinetic energy shape factor for lower surface of airfoil.
`shape_k_upper`()	Return the kinetic energy shape factor for upper surface of airfoil.
`u_e_lower`()	Return the velocities for lower surface of airfoil.
`u_e_upper`()	Return the velocities for upper surface of airfoil.
`u_e_wake`()	Return the velocities for airfoil wake.
`upper`(i)	Return the specified data on the upper surface of airfoil.
`upper_count`()	Return number of points on the upper surface of airofil.
`wake`(i)	Return the specified airfoil wake data.
`wake_count`()	Return number of points in the airofil wake.
`x_lower`()	Return the chord locations for lower surface of airfoil.
`x_upper`()	Return the chord locations for upper surface of airfoil.
`x_wake`()	Return the chord locations for airfoil wake.
`y_lower`()	Return the normal locations for lower surface of airfoil.
`y_upper`()	Return the normal locations for upper surface of airfoil.
`y_wake`()	Return the normal locations for airfoil wake.

Attributes

`alpha`	Angle of attack, in radians, for case.
`c`	Chord length in [m] of airfoil.
`filename`	Name of file containing XFoil dump data.
`n_trans`	Amplification factor used in transition model.
`name`	Name airfoil being analyzed.
`reynolds`	Reynolds number based on airfoil chord length for case.
`u_ref`	Reference velocity in [m/s] for case.
`x_trans_lower`	Chord location of boundary layer transition on lower surface.
`x_trans_upper`	Chord location of boundary layer transition on upper surface.

property name: str: Name airfoil being analyzed.

property alpha: float: Angle of attack, in radians, for case.

property u_ref: float: Reference velocity in [m/s] for case. Must be greater than zero.

property c: float: Chord length in [m] of airfoil. Must be greater than zero.

property reynolds: float: Reynolds number based on airfoil chord length for case. Must be greater than zero. If zero then the solution is assumed inviscid.

property n_trans: float: Amplification factor used in transition model. Must be greater than zero.

property x_trans_upper: float: Chord location of boundary layer transition on upper surface.

property x_trans_lower: float: Chord location of boundary layer transition on lower surface.

property filename: str: Name of file containing XFoil dump data.

upper_count()

Return number of points on the upper surface of airofil.

Returns:: Number of points on the upper surface of airfoil.
Return type:: int

lower_count()

Return number of points on the lower surface of airofil.

Returns:: Number of points on the lower surface of airfoil.
Return type:: int

wake_count()

Return number of points in the airofil wake.

Returns:: Number of points in the airfoil wake.
Return type:: int

upper(i)

Return the specified data on the upper surface of airfoil.

Parameters:: i (int) – Index of point.
Returns:: Upper airfoil surface data.
Return type:: AirfoilData

lower(i)

Return the specified data on the lower surface of airfoil.

Parameters:: i (int) – Index of point.
Returns:: Lower airfoil surface data.
Return type:: AirfoilData

wake(i)

Return the specified airfoil wake data.

Parameters:: i (int) – Index of point.
Returns:: Airfoil wake data.
Return type:: AirfoilData

s_upper()

Return arc-length distances from stagnation point for upper surface.

Returns:: Arc-length distances from the stagnation point for the upper surface.
Return type:: numpy.ndarray

s_lower()

Return arc-length distances from stagnation point for lower surface.

Returns:: Arc-length distances from the stagnation point for the lower surface.
Return type:: numpy.ndarray

s_wake()

Return arc-length distances from airfoil trailing edge.

Returns:: Arc-length distances from the airfoil trailing edge.
Return type:: numpy.ndarray

x_upper()

Return the chord locations for upper surface of airfoil.

Returns:: Chord locations for upper surface of airfoil.
Return type:: numpy.ndarray

x_lower()

Return the chord locations for lower surface of airfoil.

Returns:: Chord locations for lower surface of airfoil.
Return type:: numpy.ndarray

x_wake()

Return the chord locations for airfoil wake.

Returns:: Chord locations for airfoil wake.
Return type:: numpy.ndarray

y_upper()

Return the normal locations for upper surface of airfoil.

Returns:: Normal locations for upper surface of airfoil.
Return type:: numpy.ndarray

y_lower()

Return the normal locations for lower surface of airfoil.

Returns:: Normal locations for lower surface of airfoil.
Return type:: numpy.ndarray

y_wake()

Return the normal locations for airfoil wake.

Returns:: Normal locations for airfoil wake.
Return type:: numpy.ndarray

u_e_upper()

Return the velocities for upper surface of airfoil.

Returns:: Nondimensionalized velocities for upper surface of airfoil.
Return type:: numpy.ndarray

u_e_lower()

Return the velocities for lower surface of airfoil.

Returns:: Nondimensionalized velocities for lower surface of airfoil.
Return type:: numpy.ndarray

u_e_wake()

Return the velocities for airfoil wake.

Returns:: Nondimensionalized velocities for airfoil wake.
Return type:: numpy.ndarray

delta_d_upper()

Return the displacement thicknesses for upper surface of airfoil.

Returns:: Displacement thicknesses for upper surface of airfoil.
Return type:: numpy.ndarray

delta_d_lower()

Return the displacement thicknesses for lower surface of airfoil.

Returns:: Displacement thicknesses for lower surface of airfoil.
Return type:: numpy.ndarray

delta_d_wake()

Return the displacement thicknesses for airfoil wake.

Returns:: Displacement thicknesses for airfoil wake.
Return type:: numpy.ndarray

delta_m_upper()

Return the momentum thicknesses for upper surface of airfoil.

Returns:: Momentum thicknesses for upper surface of airfoil.
Return type:: numpy.ndarray

delta_m_lower()

Return the momentum thicknesses for lower surface of airfoil.

Returns:: Momentum thicknesses for lower surface of airfoil.
Return type:: numpy.ndarray

delta_m_wake()

Return the momentum thicknesses for airfoil wake.

Returns:: Momentum thicknesses for airfoil wake.
Return type:: numpy.ndarray

delta_k_upper()

Return the kinetic energy thicknesses for upper surface of airfoil.

Returns:: Kinetic energy thicknesses for upper surface of airfoil.
Return type:: numpy.ndarray

delta_k_lower()

Return the kinetic energy thicknesses for lower surface of airfoil.

Returns:: Kinetic energy thicknesses for lower surface of airfoil.
Return type:: numpy.ndarray

shape_d_upper()

Return the displacement shape factor for upper surface of airfoil.

Returns:: Displacement shape factor for upper surface of airfoil.
Return type:: numpy.ndarray

shape_d_lower()

Return the displacement shape factor for lower surface of airfoil.

Returns:: Displacement shape factor for lower surface of airfoil.
Return type:: numpy.ndarray

shape_d_wake()

Return the displacement shape factor for airfoil wake.

Returns:: Displacement shape factor for airfoil wake.
Return type:: numpy.ndarray

shape_k_upper()

Return the kinetic energy shape factor for upper surface of airfoil.

Returns:: Kinetic energy shape factor for upper surface of airfoil.
Return type:: numpy.ndarray

shape_k_lower()

Return the kinetic energy shape factor for lower surface of airfoil.

Returns:: Kinetic energy shape factor for lower surface of airfoil.
Return type:: numpy.ndarray

c_f_upper()

Return the skin friction coefficient for upper surface of airfoil.

Returns:: Skin friction coefficient for upper surface of airfoil.
Return type:: numpy.ndarray

c_f_lower()

Return the skin friction coefficient for lower surface of airfoil.

Returns:: Skin friction coefficient for lower surface of airfoil.
Return type:: numpy.ndarray

mass_defect_upper()

Return the mass defect for upper surface of airfoil.

Returns:: Mass defect for upper surface of airfoil.
Return type:: numpy.ndarray

mass_defect_lower()

Return the mass defect for lower surface of airfoil.

Returns:: Mass defect for lower surface of airfoil.
Return type:: numpy.ndarray

mom_defect_upper()

Return the momentum defect for upper surface of airfoil.

Returns:: Momentum defect for upper surface of airfoil.
Return type:: numpy.ndarray

mom_defect_lower()

Return the momentum defect for lower surface of airfoil.

Returns:: Momentum defect for lower surface of airfoil.
Return type:: numpy.ndarray

ke_defect_upper()

Return the kinetic energy defect for upper surface of airfoil.

Returns:: Kinetic energy defect for upper surface of airfoil.
Return type:: numpy.ndarray

ke_defect_lower()

Return the kinetic energy defect for lower surface of airfoil.

Returns:: Kinetic energy defect for lower surface of airfoil.
Return type:: numpy.ndarray