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Shock Tunnel Experiments and CFD Simulation of Lateral Jet Interaction in Hypersonic Flows

  • M. Havermann
  • F. Seiler
  • P. Hennig
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume 112)

Summary

An experimental and numerical study of lateral jet interference with hypersonic cross flows was performed at ISL. The experiments were conducted with a generic high-velocity missile model in the ISL high-energy shock tunnel STA at Mach numbers of 4.5 and 6. For each Mach number two duplicated atmospheric altitude conditions, three angles of attack and three side jet pressure ratios were studied. The flow was visualized using differential interferometry and the surface pressure was measured with fast response pressure gauges. In parallel, a numerical simulation with a CFD code was done and the calculations were validated by the experiments. The CFD simulation allowed calculating the jet interaction amplification for the different experimental flow parameters.

Keywords

Mach Number Hypersonic Flow Shock Tunnel Separation Shock Wollaston Prism 
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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References

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Copyright information

© Springer-Verlag Berlin Heidelberg 2010

Authors and Affiliations

  • M. Havermann
    • 1
  • F. Seiler
    • 1
  • P. Hennig
    • 2
  1. 1.French-German Research Institute of Saint-Louis (ISL)Saint-LouisFrance
  2. 2.LFK Lenkflugkörpersysteme GmbHUnterschleißheimGermany

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