RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.infl_coeff
infl_coeff#
- infl_coeff(x, y, xbar, ybar, st, ct, npanel, ncases, ncpts)[source]#
Compute the matrix of aerodynamic influence coefficients for later use
Assumptions: None
Source: None
Inputs x - Vector of x coordinates of the surface nodes [unitless] y - Vector of y coordinates of the surface nodes [unitless] xbar - x-coordinate of the midpoint of each panel [unitless] ybar - y-coordinate of the midpoint of each panel [unitless] st - np.sin(theta) for each panel [radians] ct - np.cos(theta) for each panel [radians] npanel - Number of panels on the airfoil [unitless]
Outputs ainfl - Aero influence coefficient matrix [unitless]
Properties Used: N/A