Fixes an equation error in the camber derivative when calculating the geometry from a NACA 4-digit airfoil.
Uses an alternative method for calculating the surface points in the function get_outline_points when the airfoil is a NACA with a parabolic flap, that ensures N number of points and either cosine clustering or even spacing of points along the chord line without deviation.
Also, when the airfoil is a NACA with a parabolic flap, it sets the default for the vertical flap hinge point to be on the camber line
Fixes an equation error in the camber derivative when calculating the geometry from a NACA 4-digit airfoil.
Uses an alternative method for calculating the surface points in the function get_outline_points when the airfoil is a NACA with a parabolic flap, that ensures N number of points and either cosine clustering or even spacing of points along the chord line without deviation.
Also, when the airfoil is a NACA with a parabolic flap, it sets the default for the vertical flap hinge point to be on the camber line