Volume 19, Issue 2 (2019)                   Modares Mechanical Engineering 2019, 19(2): 447-456 | Back to browse issues page

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1- Aerodynamics Department, Aerospace Faculty, Malek Ashtar University of Technology, Tehran, Iran
2- Aerodynamics Department, Aerospace Faculty, Malek Ashtar University of Technology, Tehran, Iran , hparhiz@mut.ac.ir
Abstract:   (1321 Views)
Today, the effects of three-dimensional flow near the blade and wing tip in the turbomachinery industry, such as rotor helicopters, turbine, as well as wings optimization in the airline industry, for safe flight with high maneuverability, are the focus of the industry in this area. Stall can be considered an influential phenomenon in this field. In the present study, the flow separation control was investigated by a vortex generator on a wing of a radar invader UAV, including a Naca64a210 airfoil with a 5° washout angle at the wing tip and integrated wings and attached to the body with a 47° sweep angle in the subsonic flow. The turbulent flow was solved by the kw-sst method for attack angles ranging from 5-20° and speeds of 30 and 60 m/sec. The results show a good fit with numerical and experimental results so that the pressure distribution curves indicate the growth of pressure in the vortex generating regions and also the areas near the tip of the wing, which results in the flow remain in the wing surface in these areas. Therefore, by examining the pitching moment and velocity contours, it can be seen that the flow separation from the 15° angle of attack, has been delayed to 20°, and also the ability to control the separation of flow along with the growth of velocities has been achieved.
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Article Type: Original Research | Subject: Computational Fluid Dynamic (CFD)
Received: 2018/05/3 | Accepted: 2018/10/24 | Published: 2019/02/2

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