Abstract:
In this thesis the result of experimental study of flow velocity and direction around NACA
0012 and NACA 0015 airfoil has been described. A closed loop wind tunnel was used to
conduct the experiment with a constant flow velocity of 15 m/s and different Angle of
Attack- 0 degree, 5 degree, 10 degree, 15 degree. Pitot tube was used to measure the
upstream velocity. Again yaw meter was used to collect and calculated data of flow velocity
and direction around airfoil. The reverse flow was found to occur at the trailing edge of the
airfoil. The results shows that if a constant flow velocity applies at two different symmetrical
airfoils of similar chord and similar AOA, the airfoil which have more thickness than other
one can cause more reverse flow at trailing edge. So thin airfoils are more suitable than thick
airfoils.
