Experimental Investigation of Subsonic Flow Structure Perpendicular to AGARD-B Wing-Body Model

Thesubsonic flow fieldsperpendicular to AGARD-B standardwing-body model was investigated. Velocity distribution was obtained by using a hot wire anemometry on five sections at wing for investigating structure, size and position of vortexes.To investigate the effect of angle of attack, yaw angle and Reynolds number on flow structure on the wing the experiments were done at 5,6,8,10 & 12 degree angels of attack 4,8 &12 degree yaw angles and 250000 & 500000 Reynolds number in the close circuit subsonic wind tunnel of Malek Ashtar university of Isfahan. The innovation of the present study is to investigate the perpendicular flow structure of the Agard-B model in subsonic conditions and to investigate the effect of the yaw angle on the flow structurebecause previous experiments on this model are mainly carried out in supersonic conditions and without an examination of the yaw angle.Two vortex structures were formed around the wing,a longitudinal vortex which formed under the influence of the wing and a transverse vortex under the influence of body.Increasing the angle of attack caused the increase power of longitudinal vortex and increasing the yaw angel caused the increase of transverse vortex. In a certain range of Reynolds number increasing of Reynolds number had not anysignificant effect on the height of vortices.