pymead.analysis.calc_aero_data.run_xfoil

run_xfoil(xfoil_settings: dict, coords: ~numpy.ndarray, export_Cp: bool = True) -> (<class 'dict'>, <class 'str'>)

Python wrapper for XFOIL

Parameters:

• xfoil_settings (dict or XFOILSettings) – Analysis parameters for XFOIL. If a dict is used, the keys found in XFOILSettings.get_dict_rep must be specified

• coords (numpy.ndarray) – Airfoil coordinates in Selig format (counter-clockwise starting from the trailing edge upper surface).

• export_Cp (bool) – Whether to export the surface pressure coefficient distribution. Default: True

Returns:

A dictionary containing the aerodynamic performance data and the path to the XFOIL log file. The dictionary will have at least the following keys: "converged", "timed_out", "errored_out", "Cl" (lift coefficient), "Cm" (pitching moment coefficient), and "alf" (angle of attack in degrees). If run in viscous mode (visc==True), the following keys will also be included: "Cd" (drag coefficient), "Cdf" (friction drag coefficient), "Cdp" (pressure drag coefficient), and "L/D" (lift-to-drag ratio). If export_Cp==True, the key "Cp" (surface pressure coefficient distribution) will also be included. The \(C_p\) distribution is a dictionary containing the following keys, where each of the values is a one-dimensional numpy.ndarray: "x", "y", and "Cp".

Return type:

dict, str