NACA 4412 airfoil cfd analysis in Solidworks -- CFD Online Discussion Forums

March 26, 2014, 14:53

NACA 4412 airfoil cfd analysis in Solidworks

Jaimin

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Jaimin Prajapati

Join Date: Mar 2014

Posts: 1

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Hello,
I am doing CFD of NACA 4412 airfoil to find Cd and Cl...

EQ..

CL=[2*Lift force X direction]/[Density of Air*(Velocity in x direction^2)*s*chord L]

any one can suggest what is actual "S"..???
Means what area i can consider to caculate the CL...

I have attached Model and the graph of CL.

Plz help me..

Attached Images

	4412.jpg (97.2 KB, 27 views)
	10.jpg (84.2 KB, 24 views)

Attached Files

4412_10 drg.zip (72.9 KB, 7 views)

April 1, 2014, 03:20		#2
GregorS New Member Gregor Seljak Join Date: Oct 2010 Posts: 21 Rep Power: 15	s*chord L must equal wing area. So in you case, s is length of wing (in the direction perpendicular to chord.)

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