|January 20, 2014, 02:51||
not getting converges Cd, Cl at high AOA
Join Date: Dec 2013
Location: Dhaka, Bangladesh
Posts: 7Rep Power: 4
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.
|cd not converged, drag coefficient, flow over airfoil, supercritical airfoil|
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