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January 20, 2014, 02:51
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not getting converges Cd, Cl at high AOA
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New Member
rishad rizwan
Join Date: Dec 2013
Location: Dhaka, Bangladesh
Posts: 7
Rep Power: 12  |
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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