# FLow over Airfoil

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 June 12, 2012, 06:46 FLow over Airfoil #1 New Member   Premal Sheth Join Date: Jun 2012 Location: Ahmadabad, Gujarat, India Posts: 27 Rep Power: 7 I am doing case study on Flow over airfoil at Low Reynolds number. i took NACA 4412 airfoil. I found all the equations but how can i found co-efficient of lift and Drag? Can any one please tell me?

June 15, 2012, 18:49
#2
New Member

Ricardo
Join Date: May 2012
Posts: 8
Rep Power: 7
Quote:
 Originally Posted by premal I am doing case study on Flow over airfoil at Low Reynolds number. i took NACA 4412 airfoil. I found all the equations but how can i found co-efficient of lift and Drag? Can any one please tell me?
Hi,

You can calculate Cl and Cd.

Lift = 0,5*rho*V^2*S*Cl
Drag = 0,5*rho*V^2*S*Cd

Where,

rho is air density (kg/m³)
V = Velocity (m/s)
S = Area (m²)
And the Lift and Drag you can get from the post processor.

 June 15, 2012, 23:31 #3 New Member   Premal Sheth Join Date: Jun 2012 Location: Ahmadabad, Gujarat, India Posts: 27 Rep Power: 7 Thank you Sir, But How can i get Cl and Cd that is main difficulty i am facing in this case study. Are the Cl and Cd depending on Airfoil or any other shape?

 June 17, 2012, 00:52 #4 Senior Member   Mehdi Join Date: Jan 2011 Location: Iran Posts: 130 Rep Power: 9 you should calculate Cl and Cd from Cf and Cp. you can find it in "Fundamentals Of Aerodynamics" by Anderson section 1.5. If you can not find it, send me an e-mail to sent this book to you. __________________ Best Regards; Mehdi E-mail: mb.pejvak[at]Gmail[dot]com

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