Hi everyone! I'm finding experimental date of static stall problem of 2D compressible flow. As you know, in the airfoil problem, as the angle of attack increases, the Lift coefficient also increaes in a certain range. But when angle exceed a critical point, separation occurs to make Cl drop adruptly, which is called "STALL". The book of "Theory of Wing Section" by ABBOTT is the well-known reference for incompressible flow. I want the data for compressible flow. Especially I need the following cases.(Of cource, other cases are welcome)

M=0.6 Re=4.5x10^6 NACA0012 airfoil

thanks.

Hi! Check the following web site:

http://www.maths.adelaide.edu.au/app...usk/aero/foil/

For NACA0012 and others there are CL/CD coefficients for Reynoldsnumber from 1.6*10**5 to 50*10**5.

Joerg