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Unsteady transonic flow control around an airfoil in a channel

Journal of Thermal Science volume 25, pages 117–122 (2016)Cite this article

Abstract

Transonic internal flow around an airfoil is associated with self-excited unsteady shock wave oscillation. This unsteady phenomenon generates buffet, high speed impulsive noise, non-synchronous vibration, high cycle fatigue failure and so on. Present study investigates the effectiveness of perforated cavity to control this unsteady flow field. The cavity has been incorporated on the airfoil surface. The degree of perforation of the cavity is kept constant as 30%. However, the number of openings (perforation) at the cavity upper wall has been varied. Results showed that this passive control reduces the strength of shock wave compared to that of baseline airfoil. As a result, the intensity of shock wave/boundary layer interaction and the root mean square (RMS) of pressure oscillation around the airfoil have been reduced with the control method.

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Authors and Affiliations

  1. Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET), Dhaka, 1000, Bangladesh

    Md. Abdul Hamid, A. B. M. Toufique Hasan & Mohammad Ali

  2. Institute of Ocean Energy, Saga University, Saga, 840-8502, Japan

    Yuichi Mitsutake & Toshiaki Setoguchi

  3. Institute of Engineering Thermophysics, Chinese Academy of Science, P.O. Box 2706, Beijing, 100080, China

    Shen Yu

Authors
  1. Md. Abdul Hamid
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  2. A. B. M. Toufique Hasan
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  3. Mohammad Ali
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  4. Yuichi Mitsutake
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  5. Toshiaki Setoguchi
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  6. Shen Yu
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Hamid, M.A., Hasan, A.B.M.T., Ali, M. et al. Unsteady transonic flow control around an airfoil in a channel. J. Therm. Sci. 25, 117–122 (2016). https://doi.org/10.1007/s11630-016-0841-3

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  • DOI: https://doi.org/10.1007/s11630-016-0841-3

Keywords

  • transonic flow
  • passive control
  • shock wave oscillation