RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.chordwise_distribution
chordwise_distribution#
- chordwise_distribution(x, y, cp, al, npanel, cf, vt)[source]#
- Compute chordwise distribution of lift and drag for
an airfoil
Assumptions: None
Source: Anderson, J. D. “Fundamentals of aerodynamics 6th ed”. MCGRAW-HILL EDUCATION (2017)
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 cf - skin friction coeff over the surface of airfoil vt - tangential velocity at all nodes
Outputs: fD - chordwise distribution of drag fL - chordwise distribution of lift
- Properties Used:
N/A