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marek December 7, 2007 12:43

Wind tunnel results
 
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


Leo Lazauskas December 7, 2007 19:48

Re: Wind tunnel results
 
What book?

marek December 7, 2007 20:11

Re: Wind tunnel results
 
Book: Abbott, Theory of wing sections, Dover publications

jcolbert December 8, 2007 00:46

Re: Wind tunnel results
 
What are the numbers in the book?

marek December 8, 2007 08:32

Re: Wind tunnel results
 
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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