EXPERIMENTAL INVESTIGATION OF EFFECT OF ANGLE OF ATTACK ON REYNOLDS STRESSES IN NEAR WAKE FLOW USING OF HOTWIRE ANEMOMETER

Determination of turbulence structure and velocity fluctuating components plays an important role in understanding the aerodynamic forces exerted on a body. In this experimental work, variations of second order moments of velocity fluctuating components have been measured and reported at different angles of attack and at different distances from trailing edge. Data acquisition has been done with a hot-wire anemometer. The symmetric flat plate as a model has a rounded leading edge and a sharp trailing edge with a sweep angle of 45 . All measurements were carried out in a wind tunnel with a cross section of 305×305 mm and a maximum velocity of 40m/s . Reynolds number based on chord length is 5 10 6  . The model has been placed at angles of attack such as 0, 5, 10, 15 and 20 degrees but we have brought the results for 0, 10 and 20degrees in this paper. These experimental results have been compared with existing results and it can be observed that they have an acceptable compatibility with each other.

Keywords:

Angle of attack , Near wake , Hotwire , Reynolds stresses , Turbulence