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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2012, Vol. 33 ›› Issue (9): 1578-1586.

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Experimental Investigation on Hypersonic Interference Heating Around Surface Protuberance

ESTRUCH-SAMPER David1, BU Xueqin2,3   

  1. 1. Department of Aeronautics, Imperial College London, London SW7;
    2. AZ, UK 2.School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;
    3. Fandamental Science on Ergonomics and Environment Control Laboratory, Beihang University, Beijing 100191, China
  • Received:2011-11-07 Revised:2011-12-05 Online:2012-09-25 Published:2012-09-22

Abstract: A study is performed to understand the details of the flow and heating characteristics around surface protuberances on hypersonic bodies. Experiments are conducted in a hypersonic gun tunnel at a freestream Mach number of 8.2 and Reynolds number of 9.35?106 m-1. The thin-film heat transfer measurements are used to assess the effects of the protuberance geometry and boundary layer state on surface heating. Oil-dot visualizations and high-speed schlieren videos are additionally used to qualitatively understand the flowfield around the protuberances. The highest heating is found to the side of the protuberance in interactions in which the incoming boundary layer remains unseparated upstream of the protuberance. In fully separated interactions, the highest heating generally takes place ahead of the protuberance and can become significantly high. The dependence of the maximum heating on the incoming boundary layer state is negligible. This is believed to be caused by the 3-dimensinality of the interactions which causes the incoming laminar boundary layer to become transitional or even fully turbulent.

Key words: hypersonic, surface protuberance, interaction heating, experiments, peak heat flux

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