RCAIDE.Library.Methods.Aerodynamics.Airfoil_Panel_Method.velocity_distribution
velocity_distribution#
- velocity_distribution(qg, x, y, xbar, ybar, st, ct, alpha_2d, npanel, ncases, ncpts)[source]#
- Compute the tangential velocity distribution at the
midpoint of each panel
Source: None
Assumptions: None
Inputs:
qg - Vector of source/sink and vortex strengths [unitless] 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] al - Angle of attack in radians [radians] npanel - Number of panels on the airfoil [unitless]
Outputs:
vt_2d - Vector of tangential velocities
Properties Used: N/A