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Old   October 28, 2002, 08:46
Default airfoil drag
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aaa
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Hi

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.
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Old   November 6, 2002, 19:36
Default Re: airfoil drag
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Amid Naz
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are you sure about the value of (0.0047)? It seems vey low ..even (0.035)..
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