Application of NPLS Technique to Hypersonic Shock-Wave and Boundary Layer Interactions

  • Ming Li
  • Shi-he Yi
  • Zhi-wei Zhu
  • Lin He
Conference paper

Introduction

While flying with hypersonic speed, the aircraft vehicle will produce very strong shock wave. The interactions between shock wave and boundary layer not only increase the drag, but also produce high pressure and high aerodynamic heating. The shock wave oscillation usually appears in the inlet of engine and in the flow inside the high-speed turbine, and this phenomena can cause unsteady heating, and excite various kinds of unsteady modes to result in tired material destroy. Therefore, it is very essential to strengthen the study and set up the effective estimate or prediction method of shock wave and boundary layer interactions.

Keywords

Shock Wave Mach Number Wind Tunnel Ring Vortex Plate Model 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • Ming Li
    • 1
  • Shi-he Yi
    • 2
  • Zhi-wei Zhu
    • 1
  • Lin He
    • 2
  1. 1.Hypervelocity Aerodynamics InstituteChina Aerodynamics Research and Development CenterMianyangChina
  2. 2.National University of Defense TechnologyChang-shaChina

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