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naca-9310

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

Thickness:	10.0%
Camber:	9.0%
Trailing edge angle:	11.6^o
Lower flatness:	26.0%
Leading edge radius:	1.2%

Max C_L:	1.967
Max C_L angle:	10.0
Max L/D:	63.229
Max L/D angle:	1.5
Max L/D C_L:	1.246
Stall angle:	2.5
Zero-lift angle:	-8.5