Re: NACA 0012 answer to request

From:         ericrood@freenet.columbus.oh.us (Eric Rood)
Organization: The Greater Columbus Freenet
Date:         06 Feb 95 02:45:21 
References:   1 2
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frbrown@csupomona.edu wrote:
: 	I believe that "Theory of Wing Sections" by Abbott and Van Doenoff
: has a pressure distribution graph for the NACA 0012 airfoil. I'ld give you
: the page number but I don't have my copy with me. 

: -- 
"THEORY OF WING SECTIONS"
 NACA 0012 graphs found on pages 462-463
 NACA 0012-64 graphs on pages 464-467
page 462... Section angle of attack, alpha sub zero, degrees
page 463... Section lift coefficient, C sub L
page 464... Section angle of attack, alpha sub zero, degrees
page 465... Section lift coefficient, C sub L
page 466... Section lift coefficient, C sub L
		alpha = 0.8 (modified), C sub Li = 0.2
page 467... Section angle of attack, alpha sub zero, degrees
		alpha = 0.8 (modified), C sub Li =0.2 (continued)
Regards, Eric
-- 
Eric Rood / 170 Monterey Drive / Dublin OH  43017-1329 / 614-761-7461
                     ericrood@freenet.columbus.oh.us
       opinions are my own, subject to change by sound arguement