TEORIC LIFT Coefficient -- CFD Online Discussion Forums

January 9, 2006, 08:42	TEORIC LIFT Coefficient	#1
Andy Guest Posts: n/a	Teoric Lift coeff for thin aerofoil with AR=4 AOA(&alpha=15 degree --> 0.261 radianti for me is 1.09 calculate with mathematical law CL= 2πα / (1+2/AR) where α is in radianti Is it correct for you? THANKS Andy

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