Volume 20, Issue 2 (February 2020)
Modares Mechanical Engineering 2020, 20(2): 381-390 |
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Moshfeghi M, Shams S, Ramezani M, Hur N. Effect of Split on Flow Separation Reduction of Wind Turbine Airfoil using DES Turbulence Model. Modares Mechanical Engineering 2020; 20 (2) :381-390
URL: http://mme.modares.ac.ir/article-15-22740-en.html
URL: http://mme.modares.ac.ir/article-15-22740-en.html
1- Aerospace Engineering Department, Faculty of New Sciences & Technologies, University of Tehran, Tehran, Iran
2- Aerospace Engineering Department, Faculty of New Sciences & Technologies, University of Tehran, Tehran, Iran , shahrokh.shams@ut.ac.ir
3- Thermal, Fluids & Energy, Faculty of Mechanical Engineering, Sogang University, Seoul, Korea
2- Aerospace Engineering Department, Faculty of New Sciences & Technologies, University of Tehran, Tehran, Iran , shahrokh.shams@ut.ac.ir
3- Thermal, Fluids & Energy, Faculty of Mechanical Engineering, Sogang University, Seoul, Korea
Abstract: (2781 Views)
A horizontal axis wind turbine power generation depends upon the aerodynamic performance of its blades. Flow separation is one of the phenomena that causes power loss and consequently decreasing the wind turbine output generation. Since usually the local angle of attack in the inner and middle parts of a blade is much greater than the local angle of attack in the separation onset, the blade section encounters a highly separated flow. Hence, flow control methods are applied in order to reduce or weaken the negative effects of the separation. This paper investigates the effects of the passive flow control method for a horizontal axis wind turbine using validated three-dimensional DES (detached eddy simulation) on an S809 split airfoil. The split in the airfoil thickness causes the flow from the high-pressure zone under the lower surface is injected into the separated area over the upper surface, transporting external energy to the separated zone, hence weakening the separated area. As the result show, the overall performance of this method depends on parameters such as split locations on the airfoil pressure and suction surfaces, the direction of the jet flow with respect to the freestream wind and also the thickness of the split. In this research, two different split locations and four thickness values of 0.5, 1, 2 and 4 percent of chord length are simulated at a range of AOA from 0 to 25 degrees. Noticeably, the results demonstrate that for an appropriate split exit location, the thickness value of 2 and 4 percent of the chord are generated more lift force. The average increase of lift coefficient for these split airfoils at a high angle of attack (17, 20, 22 and 25) are 68.5 and 55.8 percent respectively.
Article Type: Original Research |
Subject:
Computational Fluid Dynamic (CFD)
Received: 2018/07/5 | Accepted: 2019/05/14 | Published: 2020/02/1
Received: 2018/07/5 | Accepted: 2019/05/14 | Published: 2020/02/1
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