Effects of Angle of Attack on Turbulent Near Wake Flow, Using Hotwire Anemometer

In this paper, the effects of angle of attack on flow behavior in the near wake of a flat plate, using a hot-wire anemometer are reported. The symmetric flat plate used has a rounded leading edge and a sharp trailing edge with a sweep angle of. All measurements were carried out in a wind tunnel with a cross sectional area of 305×305 mm and a maximum velocity of 40. The Reynolds number, based on the chord length, was. The model was placed at angles of attack 5, 10, 15, and 20 degrees. It was concluded that, although it has been shown that the logarithmic law for angle of attack of zero is validated up to distances in near wake, its validity there is decreased by increasing the angle of attack. However, this law will not be validated by going away from the trailing edge. Also, the effect of angle of attack on turbulence kinetic energy in shear layer and on drag coefficient has been investigated. The results show that the turbulent kinetic energy is enhanced by increasing the angle of attack in a certain distance from the trailing edge and its value is reduced by going away from the trailing edge at a particular angle of attack. Also, the results show how the drag coefficient is increased when angle of attack gets larger.