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Analytical and Numerical Study of Three Shock Configurations with Negative Reflection Angle

  • L. G. Gvozdeva
  • V. L. Borsch
  • S. A. Gavrenkov

Introduction

The three-shock configuration is quite typical for the aircraft internal and external aerodynamics. For example, it appears at supersonic steady free-stream conditions in intakes (Fig. 1, left) and unsteady shock wave reflection from 2D wedges (Fig. 1, right). In the latter case the resulting flow is experimentally proven to be pseudo-stationary, and the triple point trajectory makes the constant angle χ with respect to the 2D wedge surface.

Keywords

Shock Wave Mach Number Mach Stem Mach Shock Triple Point Trajectory 
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Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • L. G. Gvozdeva
    • 1
  • V. L. Borsch
    • 2
  • S. A. Gavrenkov
    • 1
  1. 1.Joint Institute for High Temperature of RASMoscowRussia
  2. 2.Faculty of Mechanics and MathematicsDnepropetrovsk National UniversityDnepropetrovskUkraine

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