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Shock Waves pp 935-940 | Cite as

Study on the high speed scramjet characteristics at Mach 10 to 15 flight condition

  • M. Takahashi
  • K. Itoh
  • H. Tanno
  • T. Komuro
  • T. Sunami
  • K. Sato
  • S. Ueda
Conference paper

Abstract

A scramjet engine model, designed to establish steady and strong combustion at free-stream conditions corresponding to Mach 12 flight, was tested in a large free-piston driven shock tunnel. Combustion tests of a previous engine model showed that combustion heat release obtained in the combustor was not sufficient to maintain strong combustion. For a new scramjet engine model, the inlet compression ratio was increased to raise the static temperature and density of the flow at the combustor entrance. As a result of the aerodynamic design change, the pressure rise due to combustion increased and the duration of strong combustion conditions in the combustor was extended. A hyper-mixer injector designed to enhance mixing and combustion by introducing streamwise vortices was applied to the new engine model. The results showed that the hyper mixer injector was very effective in promoting combustion heat release and establishing steady and strong combustion in the combustor.

Keywords

Pressure Rise Fuel Injector Streamwise Vortex Flight Condition Engine 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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References

  1. 1.
    K. Itoh, S. Ueda, H. Tanno, T. Komuro, K. Sato: Hypersonic aerothermodynamics and scramjet research using high enthalpy shock tunnel. Shock Waves 12, 93 (2002)ADSCrossRefGoogle Scholar
  2. 2.
    M. Takahashi, K. Itoh, H. Tanno, T. Komuro, K. Sato, T. Sunami: ‘Study on Fundamental Characteristics of a Scramjet Engine at a High Speed Flight Condition’. In: Proceedings of the HI 5 Japanese Symposium on Shock Waves 2004, In Japanese Google Scholar
  3. 3.
    T. Sunami, K. Itoh, S. Onaya, K. Sato, T. Komuro, M. Takahashi: ‘Scramjet Combustion Characteristics at Mach 8–15 Flight Enthalpies(II)’. In: Proceedings of the H15 Japanese Symposium on Shock Waves 2004, In Japanese Google Scholar
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    J. A. Lordi, R. E. Mates, J. R. Mossele: Computer Program for Numerical Solution of Nonequilibrium Expansions of Reacting Gas Mixtures. NASA CR-472 (1966)Google Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • M. Takahashi
    • 1
  • K. Itoh
    • 1
  • H. Tanno
    • 1
  • T. Komuro
    • 1
  • T. Sunami
    • 1
  • K. Sato
    • 1
  • S. Ueda
    • 1
  1. 1.Japan Aerospace Exploration AgencyKakuda Space Propulsion CenterKakuda, MiyagiJapan

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