| Computations of unsteady transonic flow over airfoil at low Reynolds number |
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| 作者姓名： | ZHU Hai-tao SHAN Peng |
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| 作者单位： | School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| 基金项目： | ProgrammeofIntroducingTalentsofDisciplinetoUniversities(B08009) |
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| 摘 要： | Transonic flow over a thin airfoil at low Reynolds number was studied numerically by directly solving two-dimensional full Navier-Stokes equations through 5th order weighted essentially non-oscillatory(WENO) scheme without using any turbulence model.A series of distinguished unsteady phenomena for a thin 2-D transonic airfoil flow were presented.Due to continuous adverse pressure gradient in the subsonic flow downstream of the sonic line, the unsteady separated boundary layer with main vortex and secondary vortex was developed at the rear of the airfoil.At the trailing edge,the vortex-shedding was characterized by periodical connection of the main vortex and secondary vortex on the other side of the airfoil.The unsteady separation and vortex-shedding occurred with the same period.On the airfoil surface,the average pulse pressure related to the unsteady supersonic region was obviously smaller than that related to the vortex-shedding at the trailing edge.With the attack angle increasing from 0° to 2°, the frequency of vortex-shedding decreases about 4.2%.At last, the turbulence intensity and many second-order statistics in the wake region were investigated.
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| 关 键 词： | transonic flow unsteady flow direct numerical simulation(DNS) unsteady separation airfoil vortex-shedding |
| 收稿时间： | 2012/5/29 0:00:00 |
Computations of unsteady transonic flow over airfoil at low Reynolds number |
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| ZHU Hai-tao,SHAN Peng.Computations of unsteady transonic flow over airfoil at low Reynolds number[J].Journal of Aerospace Power,2013,28(3):646-658. |
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| Authors: | ZHU Hai-tao and SHAN Peng |
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| Institution: | School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Transonic flow over a thin airfoil at low Reynolds number was studied numerically by directly solving two-dimensional full Navier-Stokes equations through 5th order weighted essentially non-oscillatory(WENO) scheme without using any turbulence model.A series of distinguished unsteady phenomena for a thin 2-D transonic airfoil flow were presented.Due to continuous adverse pressure gradient in the subsonic flow downstream of the sonic line, the unsteady separated boundary layer with main vortex and secondary vortex was developed at the rear of the airfoil.At the trailing edge,the vortex-shedding was characterized by periodical connection of the main vortex and secondary vortex on the other side of the airfoil.The unsteady separation and vortex-shedding occurred with the same period.On the airfoil surface,the average pulse pressure related to the unsteady supersonic region was obviously smaller than that related to the vortex-shedding at the trailing edge.With the attack angle increasing from 0° to 2°, the frequency of vortex-shedding decreases about 4.2%.At last, the turbulence intensity and many second-order statistics in the wake region were investigated. |
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| Keywords: | transonic flow unsteady flow direct numerical simulation(DNS) unsteady separation airfoil vortex-shedding CLC number: V231 Document code: A |
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