RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.panel_geometry
panel_geometry#
- panel_geometry(x, y, npanel, ncases, ncpts)[source]#
Computes airfoil surface panelization parameters for later use in the computation of the matrix of influence coefficients.
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] npanel - Number of panels on the airfoil [unitless]
Outputs: l - Panel lengths [unitless] st - np.sin(theta) for each panel [radians] ct - np.cos(theta) for each panel [radians] xbar - x-coordinate of the midpoint of each panel [unitless] ybar - y-coordinate of the midpoint of each panel [unitless]
Properties Used: N/A