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naca-9512

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

Thickness:	12.0%
Camber:	9.0%
Trailing edge angle:	13.5^o
Lower flatness:	36.7%
Leading edge radius:	1.7%

Max C_L:	2.222
Max C_L angle:	11.5
Max L/D:	61.045
Max L/D angle:	4.0
Max L/D C_L:	1.627
Stall angle:	-0.5
Zero-lift angle:	-10.0