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

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Old   September 6, 1999, 21:50
Default Searchintg Exp. Data of 2D compressible Flow in static stall
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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

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Old   September 8, 1999, 10:47
Default Re: Searchintg Exp. Data of 2D compressible Flow in static stall
Joerg Weidenfeller
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Hi! Check the following web site:

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

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