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Science China Technological Sciences

, Volume 61, Issue 7, pp 1056–1071 | Cite as

Numerical exploration on jet oscillation mechanism of counterflowing jet ahead of a hypersonic lifting-body vehicle

  • Fan Deng
  • Feng Xie
  • Wei Huang
  • Hao Dong
  • Dong Zhang
Article
  • 72 Downloads

Abstract

Numerical investigation of a supersonic jet from the nose of a lifting-body vehicle opposing a hypersonic flow with the freestream Mach number being 8.0 at 40 km altitude was carried out by solving the three-dimensional, time-accurate Navier-Stokes equations with a hybrid meshes approach. Based on the analysis of the flow field structures and aerodynamic characteristics, the behaviours relevant to the LPM jet were discussed in detail, including the drag reduction effect, the periodic oscillation and the feedback loop. The obtained results show that the flow oscillation characteristic of the LPM jet is low-frequency and high-amplitude while that of the SPM jet is high-frequency and low-amplitude. Compared with the clearly dominant frequencies of the LPM jet, the SPM jet exhibits a broad-band structure. The LPM jet can sustain drag reduction effect until the angle of attack is 8°, and the lift-to-drag ratio of the vehicle is effectively improved by 6.95% at angle of attack of 6°. The self-sustained oscillation process was studied by a typical oscillating cycle of the drag force coefficient and the variation of the instantaneous pressure distribution, which reveals an off-axial flapping motion of the conical shear layer. The variation of the subsonic recirculation zone ahead of the vehicle nose strengthens the understanding of the jet behavior including the source of instability in the long penetration mode and the mechanism of the feedback loop. The aim of this paper is to advance the technology readiness level for the counterflowing jet applied as an active control technology in hypersonic flows by gaining a better insight of the flow physics.

Keywords

hypersonic lifting-body vehicle counterflowing jet LPM periodic oscillation 

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Notes

Acknowledgments

This work was supported by the Aerospace International Innovation Talent Cultivation Project of Program China Scholarship Council and the National Natural Science Foundation of China (Grant No. 11502291). This work was funded to support the first author to conduct the research as an academic visitor at the University of Sheffield in collaboration with domestic research team.

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Copyright information

© Science China Press and Springer-Verlag GmbH Germany, part of Springer Nature 2017

Authors and Affiliations

  • Fan Deng
    • 1
  • Feng Xie
    • 2
  • Wei Huang
    • 3
  • Hao Dong
    • 4
  • Dong Zhang
    • 5
  1. 1.Science and Technology on Space Physics LaboratoryChina Academy of Launch Vehicle TechnologyBeijingChina
  2. 2.Hypervelocity Aerodynamics InstituteChina Aerodynamics Research and Development CenterMianyangChina
  3. 3.Science and Technology on Scramjet LaboratoryNational University of Defense TechnologyChangshaChina
  4. 4.College of Aerospace EngineeringNanjing University of Aeronautics and AstronauticsNanjingChina
  5. 5.National Key Laboratory of Aerospace Flight DynamicsNorthwestern Polytechnical UniversityXi’anChina

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