NACA6409 results -- CFD Online Discussion Forums

June 9, 2014, 05:48	NACA6409 results	#1
samkam786 New Member Samir Join Date: Jun 2014 Posts: 4 Rep Power: 11	Hey , I've been working on the airfoil NACA 6409. The Cl value which i got is 0.67725 and Cd is 0.0098 . Can anyone tell me if these values are okay for reynold's number 3 million and inlet velocity 43.84 m/s. Thanks

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