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:   (533 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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Received: 2018/05/3 | Accepted: 2018/10/24 | Published: 2019/02/2

References
1. Pape AL, Costes M, Joubert G, David F, Deluc JM. Dynamic stall control using deployable leading-edge vortex generators. AIAA Journal. 2012;50(10):2135-2145. [Link] [DOI:10.2514/1.J051452]
2. Mumtaz Qadri MN, Shahzad A, Hamdani H, Parvez K. Dynamic stall control through passive devices in hybrid configuration. 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Grapevine, Texas: American Institute of Aeronautics and Astronautics; 2013. [Link]
3. Tianyu L, Xiaosheng W. Numerical calculation effects of deforming leading edge on airfoil dynamic stall control. Acta Aeronauticaet Astronautica Sinica (AAAS). 2014;35(4):986-994. [Link]
4. Chen K, Liang H. Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation. Chinese Physics B. 2015;25. [Link]
5. Xu H, Xing S, Ye Z. Numerical simulation of the effect of a co-flow jet on the wind turbine airfoil aerodynamic characteristics. 7th International Conference on Fluid Mechanics, ICFM7. Amsterdam: Elsevier; 2015. pp. 706-710. [Link]
6. Taylor HD. The elimination of diffuser separation by vortex generators, Report No.R-4012-3. [Internet]. Moscow: United Aircraft Corporation; 1947 [cited 2018 April 1]. Available from: Not Found [Link]
7. Schubauer GB, Spangenberg WG. Forced mixing in boundary layers. Journal of Fluid Mechanics. 1960;8(1):10-32. [Link] [DOI:10.1017/S0022112060000372]
8. Pearcey HH. Introduction to Shock-Induced Separation and its Prevention by Design and Boundary Layer Control. In: Lachman GV, editor. Boundary Layer and Flow Control, Its Principal and Applications. Oxford: Pergamon; 1961. pp. 1166-1344. [Link] [DOI:10.1016/B978-1-4832-1323-1.50021-X]
9. Bragg MB, Gregorek GM. Experimental study of airfoil performance with vortex generators. Journal of Aircraft. 1987;24(5):305-309. [Link] [DOI:10.2514/3.45445]
10. Lin J, Howard F, Bushnell D, Selby G. Investigation of several passive and active methods for turbulent flow separation control. 21st Fluid Dynamics, Plasma Dynamics and Lasers Conference. Seattle: American Institute of Aeronautics and Astronautics; 1990. [Link]
11. Lin J, Howard F, Selby G. Exploratory study of vortex-generating devices for turbulent flow separation control. 29th Aerospace Sciences Meeting. Reno: American Institute of Aeronautics and Astronautics; 1991. [Link] [DOI:10.2514/6.1991-42]
12. Lin J. Control of turbulent boundary-layer separation using micro-vortex generators. 30th Fluid Dynamics Conference, Fluid Dynamics and Co-located Conferences. Norfolk: American Institute of Aeronautics and Astronautics; 1999. [Link] [DOI:10.2514/6.1999-3404]
13. Shan H, Jiang L, Liu C, Love M, Maines B. Numerical study of passive and active flow separation control over a NACA0012 airfoil. Computers & Fluids. 2008;37(8):975-992. [Link] [DOI:10.1016/j.compfluid.2007.10.010]
14. Delnero JS, Mara-ón J, Leo D, Camocardi M, François D, Colman J. Vortex generators effect on low Reynolds number airfoils in turbulent flow. BBAA VI International Colloquium on: Bluff Bodies Aerodynamics & Applications. Milano, Italy: BBAA VI; 2008. [Link]
15. Uthandi A, Yogaraj S, Rajasekar R. Passive flow control over NACA0012 aerofoil using vortex generators. 37th National and 4th International Conference on Fluid Mechanics and Fluid Power. Chennai, India: Indian Institute of Technology Madras; 2010. [Link]
16. Delnero JS, Di Leo JM, Ezequiel Camocardi M; Martinez MA, Colman Lerner JL. Experimental study of vortex generators effects on low Reynolds number airfoils in turbulent flow [Link]
17. Shim H, Park SO. Passive control of pitch-break of a BWB UCAV model using vortex generator. Journal of Mechanical Science and Technology. 2015;29(3):1103-1109. [Link] [DOI:10.1007/s12206-015-0222-y]
18. Park S, Chang K, Ko A. Numerical simulation of the low speed aerodynamic characteristics for BWB type UCAV configuration with -5 degree twisted angle. 35th AIAA Applied Aerodynamics Conference. Reston: AIAA AVIATION Forum; 2017. [Link]