Searchintg Exp. Data of 2D compressible Flow in static stall
 

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.

Re: Searchintg Exp. Data of 2D compressible Flow in static stall
 

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