airfoilprep.Airfoil.correction3D¶

Airfoil.correction3D(r_over_R, chord_over_r, tsr, alpha_max_corr=30, alpha_linear_min=-5, alpha_linear_max=5)[source]¶

apply 3-D rotational corrections to each polar in airfoil

Parameters:

r_over_R : float: radial position / rotor radius
chord_over_r : float: local chord / local radius
tsr : float: tip-speed ratio
alpha_max_corr : float, optional (deg): maximum angle of attack to apply full correction
alpha_linear_min : float, optional (deg): angle of attack where linear portion of lift curve slope begins
alpha_linear_max : float, optional (deg): angle of attack where linear portion of lift curve slope ends

Returns: