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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2022, Vol. 43 ›› Issue (1): 626104-626104.doi: 10.7527/S1000-6893.2021.26104

• Special Topic of Shock/Boundary Layer Interation Mechanism and Control • Previous Articles     Next Articles

Experiment on interaction between supersonic turbulent boundary layer and cylinder

GANG Dundian, YI Shihe, MI Qi, NIU Haibo   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • Received:2021-07-14 Revised:2021-09-24 Online:2022-01-15 Published:2021-09-22
  • Supported by:
    National Key R&D Program of China (2019YFA0405300); National Natural Science Foundation of China (11902354)

Abstract: The flow field of interactions between the turbulent boundary layer and cylinders was studied in a supersonic wind tunnel with the Mach numbers 3.4 and 3.8 respectively. The cylinder was mounted on the floor of the test section, and the boundary layer was fully developed at the installation position. Besides, the influence of the diameter and height of the cylinders on the flow field structure and pressure fluctuations was studied, and the fine structures of the flow field in the streamwise and the spanwise plane were obtained using Nano-tracer Planar Laser Scattering(NPLS) technique. The shock system and the horseshoe vortex structure could be clearly distinguished. It could be found that the interactions between the shock wave and the turbulence structures presented unsteady characteristics through images of the spanwise plane. The dynamic pressure transducers were used to measure the pressure pulsation characteristics of the interaction region in front of the cylinder. In the shock foot region, the pressure pulsation characteristics ranged from 11 kHz to 38 kHz, which was speculated to be mainly caused by the interactions between shock foot and vortex structure, and the breakup of vortex structures in the stagnation region. With increasing height, the characteristic frequency corresponding to the peak value of the measuring point near the shock foot decreased. The energy enhancement in the low frequency range of 0-3 kHz was found at the upstream points, which was mainly caused by the separation zone, indicating that the increase of height enhanced the flow separation.

Key words: supersonic flow over cylinders, shock wave/boundary layer interactions, unsteady characteristics, pressure fluctuations, NPLS

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