Laminar flow past oscillating Naca 0012 airfoil

kafkaf · April 6, 2009, 14:45

Gentlemen,

I have to validate a new Dual Time Stepping algorithm. Mach number should be less than 0.3 and flow is laminar (Re~1000 to 20000).

I will be grateful if anyone could email me any decent paper presenting CL,Cd,Cm variation with angle of attack for oscillating Naca 0012 airfoil.

Thanks in advance

harishg · April 7, 2009, 02:49

You can use Garrick's formula to compare your results. The formula works well as long as you do not have any flow separation. The paper is available from NASA server or you can look for dissertation of Young through google. Both of them will furnish you the analytical expressions. For a more detailed comparison, you can look for experiments by Lai and Platzer.

April 6, 2009, 14:45	Laminar flow past oscillating Naca 0012 airfoil	#1
kafkaf New Member Join Date: Apr 2009 Posts: 3 Rep Power: 17	Gentlemen, I have to validate a new Dual Time Stepping algorithm. Mach number should be less than 0.3 and flow is laminar (Re~1000 to 20000). I will be grateful if anyone could email me any decent paper presenting CL,Cd,Cm variation with angle of attack for oscillating Naca 0012 airfoil. Thanks in advance

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April 7, 2009, 02:49		#2
harishg Senior Member N/A Join Date: Mar 2009 Posts: 189 Rep Power: 17	You can use Garrick's formula to compare your results. The formula works well as long as you do not have any flow separation. The paper is available from NASA server or you can look for dissertation of Young through google. Both of them will furnish you the analytical expressions. For a more detailed comparison, you can look for experiments by Lai and Platzer.