• Nirav Prajapati
• Dr. Umang Patdiwala
• Piyushkumar Surani

A wind tunnel test was conducted on a NACA 6409 airfoil in order to determine an angle of attack with -15˚, -10˚, -5˚, 0˚, 5˚, 10˚ and 15˚ . This Airfoil is designed in the CREO V.6 and printed in the 3D printer for the taken different experimental value. The coefficient of pressure was obtained from the upper surface and lower surface of the airfoil using multi tube pressure head manometer. Lift coefficient and Drag coefficient were measured at the 14.27 m/s velocity in the free stream test section at the various angle of attack. Experimental validation of the airfoil is carried out with the CFD analysis of the airfoil at different angle of attack, where experimental atmosphere of the test section created in the CFD analysis.

Airfoil, Angle of attack, Lift coefficient, Drag coefficient

"EXPERIMENTAL VALIDATION OF NACA 6409 AIRFOIL USING CFD ANALYSIS", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.8, Issue 4, page no.757-764, April-2021, Available :http://www.jetir.org/papers/JETIR2104199.pdf

"EXPERIMENTAL VALIDATION OF NACA 6409 AIRFOIL USING CFD ANALYSIS", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.8, Issue 4, page no. pp757-764, April-2021, Available at : http://www.jetir.org/papers/JETIR2104199.pdf