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December 7, 2007, 11:43
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Wind tunnel results
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#1 |
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Guest
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Hello!
I run simulation for NACA 2415 airfoil up to AOA 14 deg. in CFX. I get the same drag coefficients like in books but I get higher (about 0.2) lift coefficients. Then I run simulation with the same grid and other parameters for NACA 2412. I get the same results like in book. Do you think it is possible that lift coefficients for NACA 2415 in book are not correct? Cheers |
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December 7, 2007, 18:48
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Re: Wind tunnel results
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#2 |
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Guest
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What book?
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December 7, 2007, 19:11
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Re: Wind tunnel results
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#3 |
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Guest
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Book: Abbott, Theory of wing sections, Dover publications
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December 7, 2007, 23:46
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Re: Wind tunnel results
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#4 |
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Guest
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What are the numbers in the book?
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December 8, 2007, 07:32
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Re: Wind tunnel results
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#5 |
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Guest
Posts: n/a
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Lift coefficients in book are about 0,04 lower. Difference is about 8%. But for NACA 2412 difference is only 1%. I use same grid and solver parameters in both cases.
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