RCAIDE.Library.Methods.Geometry.Airfoil.compute_naca_4series
compute_naca_4series#
- compute_naca_4series(airfoil_geometry_file, npoints=201, leading_and_trailing_edge_resolution_factor=1.5)[source]#
Computes the points of NACA 4-series airfoil
Assumptions: None
Source: None
- Inputs:
airfoils <string> npoints [unitless] leading_and_trailing_edge_resolution_factor [unitless]
Outputs: airfoil_data.
thickness_to_chord [unitless] x_coordinates [meters] y_coordinates [meters] x_upper_surface [meters] x_lower_surface [meters] y_upper_surface [meters] y_lower_surface [meters] camber_coordinates [meters]
Properties Used: N/A