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Pseudo-shock System Structure in Rectangular Laval Nozzles with Gaps

  • T. Gawehn
  • M. Giglmaier
  • J. F. Quaatz
  • A. Gülhan
  • N. A. Adams

Introduction

The acceleration of a fluid in a Laval nozzle to supersonic speed leads to a significant decrease of the static temperature in the flow, and deceleration via a normal shock results in a sudden reheating. Both effects are used within the joint project PAK 75 (Deutsche Forschungsgemeinschaft DFG) for the homogeneous ignition of a precursor and, hence, for the production of gas phase synthesized nanoparticles with narrow size distribution. However, the shock boundary layer interaction at the desired shock position leads to the formation of a so-called pseudo-shock system. Thereby, the heating rate across the shock system is reduced and the homogeneity of the particle growth is negatively affected by the inhomogeneous downstream conditions. Such pseudo-shock systems have been investigated by many research groups and a comprehensive overview is given by [1].

Keywords

Normal Shock Schlieren Image Laval Nozzle Nozzle Throat Shock System 
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

  1. 1.
    Matsuo, K., Miyazato, Y., Kim, H.-D.: Shock train and pseudo-shock phenomena in internal gas flows. Progress in Aerospace Sciences 35, 1 (1999)CrossRefGoogle Scholar
  2. 2.
    Gawehn, T., Gülhan, A., Giglmaier, M., Al-Hasan, N.S., Adams, N.A.: Analysis of Pseudo-Shock System Structure and Asymmetry in Laval Nozzles with Parallel Side Walls. In: 19th Interantional Shock Interaction Symposium, Moscow (2010)Google Scholar
  3. 3.
    Giglmaier, M., Quaatz, J.F., Gawehn, T., Gülhan, A., Adams, N.A.: Numerical and experimental investigation of the effect of bypass mass flow due to small gaps in a transonic channel flow. In: 28th International Symposium on Shock Waves, Manchester (2011)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • T. Gawehn
    • 1
  • M. Giglmaier
    • 2
  • J. F. Quaatz
    • 2
  • A. Gülhan
    • 1
  • N. A. Adams
    • 2
  1. 1.Supersonic and Hypersonic Technology Department, German Aerospace Center (DLR)Institute of Aerodynamics and Flow TechnologyCologneGermany
  2. 2.Lehrstuhl für Aerodynamik und StrömungsmechanikTechnische Universität MünchenGarchingGermany

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