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not getting converges Cd, Cl at high AOA

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Old   January 20, 2014, 02:51
Default not getting converges Cd, Cl at high AOA
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rishad rizwan
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hello all ,
i am running a simulation of super critical airfoil at transonic speed. I am getting converged results at AOA upto 4 degree which agree well with the experimental results, but at AOA 5 to 9 degree the results (Cd,Cl,Cm) becomes periodic....then again at AOA 10,11,12..results are converging.....
I'm doing steady state pressure based solution with S-A model.

can anyone tell me please whether it's natural or due to any error in my modeling ?

thanks in advance for your reply.
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cd not converged, drag coefficient, flow over airfoil, supercritical airfoil

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