NACA profile calculations

Oliver Arend schreef:
If so, what's a useable algorithm to plt intrados and extrados?

http://en.wikipedia.org/wiki/NACA_ai...t_NACA_airfoil

dy_c/dx you can get by differentiating between two arbitrarily chosen
points on the camber line. You'll probably need closer spacing of
these points near the leading edge.
So weit war ich ja schon...*

How do I calculate from the basic parameters the behaviour of the profile, i.e. the Cl curves?

What are you looking for? Slope will be very close to 2 pi ;-)
**Bis hier bin ich auch noch dabei!

The angle of attack of zero lift is -2 f/t (f/t is maximum camber relative
to chord). The cm is more difficult to estimate -- it's easiest to
just plug the airfoil into XFOIL and do the calculation

XFOIL muss es sein was mir fehlte!***

(or do you prefer
http://www.iag.uni-stuttgart.de/IAG/...lettheorie.pdf
?).

Mm, mal schauen, nur nicht gerade jetzt.****

The rest, like clmax, are viscous effects and can't simply be
deducted/estimated from the basic parameters.

Schade*****

Oliver, besten dank!
KA

* Nothing new there
** This also was more or less mastered before
*** This must be what I was missing
**** Will have a look, not right now though
***** Too bad.