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Experimental and CFD Analysis of Airfoil at Low Reynolds Number

Chandrakant Sagat , Pravin Mane, and B S Gawali
Department of Mechanical Engineering, Walchand College of Engineering, Sangli 415146.

Abstract—The determination of lift and drag of airfoil from wind tunnel measurements is discussed for incompressible flow. Calculated the upper and lower surface pressure and velocity of an airfoil is essential for calculating the forces on it. The Effects of model support are neglected. No simplifying assumptions on the flow along the test section walls are made. The purpose of load measurements on the model is to make available the forces and moments so that they may be corrected for tunnel boundary and utilized in predicting the performance of the full-scale vehicle or other device at different angle of attack from 0o to 20o and at maximum velocity 15 m/s. Airfoil analysis of the airfoil at low Reynolds no. and comparing experimental results and cfd results.

Index Terms—Airfoil, Angle of attack, CFD, Low reynolds no., Wind tunnel

Cite: Chandrakant Sagat, Pravin Mane, and B S Gawali, "Experimental and CFD Analysis of Airfoil at Low Reynolds Number," International Journal of Mechanical Engineering and Robotics Research, Vol.1, No.3, pp. 277-283, October 2012.