An Investigation On The Aerodynamics Of Symmetrical Airfoil

In the present work an aerodynamic investigation was done over a symmetrical airfoil NACA 0014. Experiments were carried out in a low speed wind tunnel and the experimental data was collected at different Reynolds number. The main objective of this experiment is to determine the aerodynamic characteristics of airfoil under the influence of Reynolds number and angle of attack. Airfoil has been tested from 0o to 18o angle of attack with 3o steps and Reynolds number from 1.49x105 to 2.98x105 . The coefficients of pressure on both the surfaces were obtained and lift and drag coefficient were calculated. Stall condition were observed at 15-16o angle of attack.