Volume 31 Issue 6
Jun.  2016
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ZHOU Xun-huang, CHEN Rong-qian, YOU Yan-cheng, ZHU Cheng-xiang, HUANG Yue. Effects of incoming boundary layer on injection characteristics of a scramjet combustor[J]. Journal of Aerospace Power, 2016, 31(6): 1351-1358. doi: 10.13224/j.cnki.jasp.2016.06.010
Citation: ZHOU Xun-huang, CHEN Rong-qian, YOU Yan-cheng, ZHU Cheng-xiang, HUANG Yue. Effects of incoming boundary layer on injection characteristics of a scramjet combustor[J]. Journal of Aerospace Power, 2016, 31(6): 1351-1358. doi: 10.13224/j.cnki.jasp.2016.06.010

Effects of incoming boundary layer on injection characteristics of a scramjet combustor

doi: 10.13224/j.cnki.jasp.2016.06.010
  • Received Date: 2015-09-17
  • Publish Date: 2016-06-28
  • Effects of incoming boundary layer on flow field characteristics and mixing performance of transverse jet in a scramjet combustor were numerically investigated by using Reynolds-averaged Navier-Stokes. Results indicate that there is a critical dynamic pressure ratio for every specific flow status. Only when the injection dynamic pressure ratio is less than that value, increasing incoming boundary layer thickness could effectively improve the jet penetration depth and mixing efficiency. Otherwise, variation of incoming boundary layer rarely affects the jet penetration depth and mixing efficiency. For the cases studied, the critical dynamic pressure ratio was around 0.900. At the same dynamic pressure ratio condition, the thick incoming boundary layer cases were only 0.93 times the total pressure recovery coefficient of the thin cases. The friction loss of imcoming boundary layer is the dominant factor affecting the total pressure recovery of the scramjet combustor, and variation of incoming boundary layer thickness makes little influence on total pressure recovery induced by the jet and its downstream flow field features.

     

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