Skip to main content
SpringerLink
Log in

An experimental study of supersonic combustion with incoming high temperature pure air stream obtained by shock tunnel

  • Conference paper
  • First Online:
Shock Waves

  • 113 Accesses

Abstract

An experimental study is conducted to investigate the phenomena of supersonic combustion by means of shock tunnel. By using shock tunnel, test air is compressed by reflected shock wave up to stagnation temperature of 2800 K and stagnation pressure of 0.35 MPa. Heated air is used as a reservoir gas of supersonic nozzle. Hydrogen is injected transversely through circular hole into freestream of Mach 2. Flow duration is 430 microseconds. By schlieren method and CCD UV camera, the effects of injection pressure to flowfield and the combustion were investigated.

This is a preview of subscription content, log in via an institution to check access.

Access this chapter

Log in via an institution
Chapter
USD 29.95
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
eBook
USD 299.00
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. R.R. Boyce, A. Pauli, R.J. Stalker, M. Wendt, N. Chinsei and H. Miyajima: Comparison of supersonic combustion between impulse and vitiation-heated facilities. Journal of Propulsion and Power 16(4), 709 (2000)

    Article  Google Scholar 

  2. R.C. Roger, D.P. Capriotti and R.W. Guy: Experimental supersonic combustion research at NASA Langley. AIAA-Paper 98-2506 (1998)

    Google Scholar 

  3. G. Smeets, C. Quenett: ‘Shock Tube Investigation of H2 Combustion in a High Temperature Supersonic Air Flow’. In: (Scramjet), Proceeding of IUTAM Symposium on Combustion in Supersonic Flows, Netherlands, 1997, pp. 173–178

    Google Scholar 

  4. B.K. McMillin, J.L. Palmer and R.K. Hanson: Temporally resolved, two-line fluorescence imaging of NO temperature in a transverse jet in a supersonic cross flow. Applied Optics 32(36), 7532 (1993)

    Article  ADS  Google Scholar 

Download references

Author information

Author notes

  1. K. Toshimitsu

    Present address: Matsue National College of Technology, Japan

Authors and Affiliations

  1. Dept. of Aeronautics and Astronautics, Kyushu University, Japan

    A. N. Hakim, S. Aso, S. Miyamoto & K. Toshimitsu

Authors
  1. A. N. Hakim
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. S. Aso
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. S. Miyamoto
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. K. Toshimitsu
    View author publications

    You can also search for this author in PubMed Google Scholar

Editor information

Editors and Affiliations

  1. Key Laboratory of High-Temperature Gas Dynamics Institute of Mechanics, Chinese Academy of Sciences, 15 Bei Si Huan Xi Rd., Beijing, 100080, P.R. China

    Z. Jiang

Rights and permissions

Reprints and permissions

Copyright information

© 2005 Tsinghua University Press and Springer-Verlag Berlin Heidelberg

About this paper

Cite this paper

Hakim, A.N., Aso, S., Miyamoto, S., Toshimitsu, K. (2005). An experimental study of supersonic combustion with incoming high temperature pure air stream obtained by shock tunnel. In: Jiang, Z. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-27009-6_146

Download citation

  • DOI: https://doi.org/10.1007/978-3-540-27009-6_146

  • Published:

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-540-22497-6

  • Online ISBN: 978-3-540-27009-6

  • eBook Packages: Physics and AstronomyPhysics and Astronomy (R0)

Publish with us

Policies and ethics

Search

Navigation