Volume 37 Issue 5
May  2022
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HE Kun, YUAN Huacheng. Drag and heat reduction characteristics and flow mechanism of typical aero-spikes[J]. Journal of Aerospace Power, 2022, 37(5): 1064-1078. doi: 10.13224/j.cnki.jasp.20210178
Citation: HE Kun, YUAN Huacheng. Drag and heat reduction characteristics and flow mechanism of typical aero-spikes[J]. Journal of Aerospace Power, 2022, 37(5): 1064-1078. doi: 10.13224/j.cnki.jasp.20210178
shu

Drag and heat reduction characteristics and flow mechanism of typical aero-spikes

doi: 10.13224/j.cnki.jasp.20210178
  • 1.

    College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • 2.

    Research Institute of Aero-Engine，Beihang University，Beijing 102206，China

  • Received Date: 2021-04-18
  • Publish Date: 2022-05-28
    Abstract
  • In order to study the relevant characteristics of drag and heat reduction for the supersonic/hypersonic blunt aircraft with an aero-spike，numerical simulation was used to study the flow characteristics of six kinds of typical configurations of spike systematically.The influence laws of length of spike and Mach number of inlet flow on flow characteristics were given，and the mechanisms of its formation were also discussed.The results showed that when the Mach number was low，five kinds of the spikes with a flow interferent at the head reached the maximum drag reduction rates when the recirculation region was about to split； when the Mach number was high，local peaks of drag reduction rates appeared before and after the recirculation region splitting，but the maximum drag reduction rates occurred at longer lengths of the spikes after the recirculation region splitting.When the Mach number was 3，the relative lengths of the six kinds of spikes were between 0.8 and 1.2 when the drag reduction rates were maximum，in comparison，the drag reduction effects of sphere-spike，hemisphere-spike and bicone-spike were the best，the maximum drag reduction rates were between 45% and 50%；the cone-spike was the worst，which was between 20% and 25% and was obviously lower than the configurations with a flow interferent at the head.When the lengths of the aero-spikes were the same，the drag reduction rates of the aerospikes with a flow interferent at the head increased with the increase of Mach number，while that of the cone-spike was opposite.The change of pressure distribution caused by recirculation region，separation shock，bow shock and local expansion flow of the flow fields was the main reason for the change of the overall resistance of the configurations.

     

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