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Volume 49 Issue 11
Nov.  2023
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Journal of Beijing University of Aeronautics and Astronautics  > 2023  >  49(11): 2913-2920.
ZHANG P H，CHEN H Y，ZHANG J，et al. Passive flow control for weapon bay at high Mach number[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（11）：2913-2920 （in Chinese） doi: 10.13700/j.bh.1001-5965.2021.0790
Citation: ZHANG P H，CHEN H Y，ZHANG J，et al. Passive flow control for weapon bay at high Mach number[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（11）：2913-2920 （in Chinese） doi: 10.13700/j.bh.1001-5965.2021.0790
shu

Passive flow control for weapon bay at high Mach number

doi: 10.13700/j.bh.1001-5965.2021.0790
  • 1.

    Computational Aerodynamic Institute of China Aerodynamics Research and Development Center，Mianyang 621000，China

  • 2.

    High Speed Aerodynamic Institute of China Aerodynamics Research and Development Center，Mianyang 621002，China

Funds:  National Numerical Windtunnel Project
More Information
  • Corresponding author: E-mail：fqzhou20@126.com
  • Received Date: 28 Dec 2021
  • Accepted Date: 20 Mar 2022
  • Publish Date: 10 May 2022
    Abstract

  • The noise generation mechanism of weapon bays at a high Mach number (Ma>2) is different from that of the subsonic, transonic, and supersonic weapon bay flow because of the stronger and more stable shear layer. This discrepancy may also lead to different flow control measures for cavity noise suppression. Using numerical simulations and wind tunnel tests, this study examines the effects of the cylindrical fuselage and Mach number on cavity flow characteristics, and of different passive flow control measures such as leading edge serrations, leading edge columns, leading edge transverse columns and leading edge baffles on the sound pressure level of a weapon bay at a high Mach number. This study provides a reference for the design and research of flow control measures for a high Mach number weapon bay. The results show that the cylindrical fuselage has an impact on the pressure distribution at the cavity bottom, that the unevenness of the pressure distribution increases, and that the pressure peak near the rear wall increases. The passive flow control measures, which are more effective for the subsonic, transonic and supersonic weapon bay flow, are not effective for the high Mach number cavity flow, and even increase the noise level in the weapon bay. Further research is needed to design more effective flow control measures.

     

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