# 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)