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naca-2308

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Generated NACA airfoil. See also http://www.aerospaceweb.org/question/airfoils/q0041.shtml

Thickness:	8.0%
Camber:	2.0%
Trailing edge angle:	9.7^o
Lower flatness:	84.0%
Leading edge radius:	0.8%

Max C_L:	0.916
Max C_L angle:	12.0
Max L/D:	43.374
Max L/D angle:	4.5
Max L/D C_L:	0.764
Stall angle:	5.5
Zero-lift angle:	-1.5