It is difficult to caculate airfoil drag precisely,could you help me.For example,cal.NACA64a216 in Fluent S-A/K-E model,alfa=0 degree,M=0.6,the cal.result drag coefficent cd=0.035. But the real cd=0.0047.
Re: airfoil drag
are you sure about the value of (0.0047)? It seems vey low ..even (0.035)..
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