generate_naca_camber¶
Defines the x and y coordinates of a 4-digit NACA profile’s camber line (i.e no thickness).
- The NACA 4-series airfoils follow the nomenclature: NACA MPTT where:
- M indicates the maximum camber \(M = 100m\)
- P indicates the position of the maximum camber \(P=10p\)
- TT indicates the thickness to chord ratio \(TT=(t/c)*100\)
param M: | maximum camber times 100 (i.e. the first of the 4 digits) |
---|---|
type M: | float |
param P: | position of the maximum camber times 10 (i.e. the second of the 4 digits) |
type P: | float |
returns: | x and y coordinates of the chosen airfoil |
rtype: | (x_vec,y_vec) |
Example
The NACA2400 airfoil would have 2% camber with the maximum at 40% of the chord and 0 thickness. To plot the camber line one would use this function as:
x_vec, y_vec = generate_naca_camber(M = 2, P = 4)