NACA profile calculations

cavelamb schreef:
jan olieslagers wrote:

And also, less poignant but still:
How do I calculate from the basic parameters the behaviour of the
profile, i.e. the Cl curves? And perhaps other nice info like the
leading edge diameter?

Generally: any pointers to in-depth information that a non-engineer
can mentally digest?

TIA,

Jan,

I'd not think the CL and CD curves can be "calculated" from the airfoil
shape
very easily. Those, and other behaviors, are usually derived from wind
tunnel
testing.

Having said that, I'd not be too surprised to find someone has written a
program
that approximates CL/CD from a database of some kind.

Anyway, question...

Are you trying to plot the airfoil shape from a table of ordinates?
Or are you trying to generate a shape from a mathematical algorythm?

My idea was to first plot a lot of ordinates through an algoritm, then
plot the airfoil around these. But it seems there is so much good work
already done that I'd be reinventing the wheel. I'll have to study all
the links given here, that'll take some doing to begin with.
But I did have understood the airfoil's behaviour could be calculated
from the parameters that describe its form - wrong assumption, apparently.
Thank you!
KA