An experimental study was conducted in order to investigate the flow field over half delta wings. These wind tunnel tests was carried out over the 70 degree swept half delta wing at angles of attack of 10 to 35 degrees between 1.5×105 and 2.5×105 Reynolds Numbers. Therefore, the effect of angle of attack’s variation and Reynolds Number’s variation was perused. The pressure contour at different cross section of the delta wing was obtained by using pitot tubes. Furthermore, by using a hot wire anemometer the turbulence intensity, average velocity, and mean kinetic energy was measured. The results show that as the angle of attack increases, the vortex core become bigger and stronger. Not only does the vortex core become bigger, but also it moves toward inside of the delta wing. The magnitude of pressure coefficient at the center of vortex is lower than the other regions. By increasing of the angle of attack the pressure coefficient at the vortex core declines more. Moreover, the results indicate that the vortex location and its breakdown are not changing with variation of Reynolds number between 1.5 and 2.5×105. In addition, the turbulence intensity, average velocity, and mean kinetic energy, obtained by the hot wire, at the vortex core are higher than the other regions.

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