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Hi, guys:
I got a problem about airfoil which puzzled me presently, for I'm
designing my midget, and for lack of wortmann laminar airfoil detailed
data which I long forward, so I've to fall back on the naca 4412
temporarily, I found two naca reports, in which indicated that 4412
could reach 0.6 at angle of attack of 2 degree under the condition of
Re=3 million and aspect ratio of 6, but in the another report which
published by Russian show the naca 4412 CL at 2 degree angle of attack
can only reach 0.45, which one is correct?? Below is the polar
graphics, the first graphic is the Russian’s.
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|Filename: NACA 4412--.JPG |
|Download: http://www.aviationbanter.com/attachment.php?attachmentid=89|
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johnnylee
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a airfoil problem
