Volume 34 Issue 11
Nov.  2019
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BAO Xingdong, YU Xilong, MAO Hongxia. Influence of rocket engine exit parameters on flow and radiation characteristics of exhaust plume[J]. Journal of Aerospace Power, 2019, 34(11): 2448-2457. doi: 10.13224/j.cnki.jasp.2019.11.017
Citation: BAO Xingdong, YU Xilong, MAO Hongxia. Influence of rocket engine exit parameters on flow and radiation characteristics of exhaust plume[J]. Journal of Aerospace Power, 2019, 34(11): 2448-2457. doi: 10.13224/j.cnki.jasp.2019.11.017
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Influence of rocket engine exit parameters on flow and radiation characteristics of exhaust plume

doi: 10.13224/j.cnki.jasp.2019.11.017
  • 1.

    State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China

  • 2.

    School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China

  • 3.

    Science and Technology on Optical Radiation Laboratory,Beijing Institute of Environmental Features,Beijing 100854,China

  • Received Date: 2019-03-03
  • Publish Date: 2019-11-28
    Abstract
  • Based on the detailed chemical reaction mechanism, the flow and radiation of the plume were studied by the method of computational fluid dynamics (CFD) + line-by-line integration and light of sight method. The effects of different chemical reaction mechanisms on flow and radiation were compared and analyzed. The validity of the model was verified by optical measurement data. On this basis, the influence of rocket exit parameters on plume flow and radiation was analyzed in detail. The results showed that: the temperature of the nozzle exit had little effect on the structure of the flow field, but had a significant effect on the afterburning; the increase of pressure at the nozzle exit had an effect on the wave structure of the Maher disk, but had little effect on the afterburning; the infrared radiation intensity of the plume increased with the increase of the temperature and pressure of the nozzle exit, and the infrared radiation intensity was positively related to the thrust of the engine.

     

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