RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.aero_coeff
aero_coeff#
- aero_coeff(x, y, cp, al, npanel)[source]#
- Compute airfoil force and moment coefficients about
the quarter chord point
Assumptions: None
Source: None
Inputs: x - Vector of x coordinates of the surface nodes y - Vector of y coordinates of the surface nodes cp - Vector of coefficients of pressure at the nodes al - Angle of attack in radians npanel - Number of panels on the airfoil
Outputs: cl - Airfoil lift coefficient cd - Airfoil drag coefficient cm - Airfoil moment coefficient about the c/4
- Properties Used:
N/A