NACA
NACA Airfoils
NACA
is a MATLAB library which
can take the parameters of certain NACA airfoils and return the
coordinates of a sequence of points that outline the wing shape.
Licensing:
The computer code and data files described and made available on this
web page are distributed under
the GNU LGPL license.
Languages:
NACA is available in
a C version and
a C++ version and
a FORTRAN77 version and
a FORTRAN90 version and
a MATLAB version.
Related Data and Programs:
Reference:

Eastman Jacobs, Kenneth Ward, Robert Pinkerton,
"The characteristics of 78 related airfoil sections from tests in
the variabledensity wind tunnel",
NACA Report 460, 1933.
Source Code:

naca4_mpt.m,
extracts the M, P and T parameters from a NACA 4 digit code.

naca4_cambered.m,
given a point xc along the camber line, returns pairs
(xu,yu) and (xl,yl) along the upper and lower airfoil surface
of a NACA cambered 4digit airfoil.

naca4_symmetric.m,
given a point x, returns the value y(x) so that (x,y(x))
lies on the upper surface of a NACA symmetric 4digit airfoil
and (x,y(x)) lies on the lower surface.

r8mat_write.m,
writes an R8MAT to a file.

timestamp.m,
prints out the current YMDHMS date as a timestamp.
Examples and Tests:
You can go up one level to
the MATLAB source codes.
Last revised on 24 May 2014.