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Volume 33 Issue 01
Jan.  2007
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Journal of Beijing University of Aeronautics and Astronautics  > 2007  >  33(01): 1-4.
Li Guohui, Deng Xueying. Influence on flow around mid-part of slender at high AOA by sweep wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(01): 1-4. (in Chinese)
Citation: Li Guohui, Deng Xueying. Influence on flow around mid-part of slender at high AOA by sweep wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(01): 1-4. (in Chinese)
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Influence on flow around mid-part of slender at high AOA by sweep wing

  • 1.

    Military Simulation Technology Institute, Aviation University of Air Force, Changchun 130022, China

  • 2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 21 Dec 2005
  • Publish Date: 31 Jan 2007
    Abstract
  • The flow around a slender was fixed in this way which a tiny pert urbation was located on the nose of the slender. The influence on flow str u cture and aerodynamic of a slender by sweep wing at high angle of attack was studied. The experimental results indicate that at angle of attack 30°,the fl ow and pressure distribution of mid-part leeside of a slender are dominated by sweep wing and forebody vortices. At angles of attack α=40°~60°, sweep wing dominates the flow around the mid-part of a slender only, and the flow of mid-p art leeside of a slender becomes full separate flow, the pressure distribution o f mid-part leeside of a slender retains constant.

     

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