Skip to main content
SpringerLink
Log in

Hypervelocity Test with a Detonation-Driven Expansion Tube

  • Conference paper
  • First Online:
31st International Symposium on Shock Waves 2 (ISSW 2017)

Included in the following conference series:

  • 1058 Accesses

Abstract

A shock-expansion tube/tunnel is a ground-based test facility to generate hypervelocity test flows for the study of atmospheric reentry physics. Such a high enthalpy test flow features thermochemically non-equilibrium which may lead to critical difficulties in flow diagnostics and measurements. In addition, the test time of such an impulse facility is extremely short which implies a requirement of transducers with high-frequency response capability for model tests or flow diagnostics. In the present work, computations for non-equilibrium reacting flow are conducted to diagnose the key flow parameters and evaluate the test flow for facility upgrading. A conic nozzle is appended to the original facility and to obtain a larger test section and larger Mach numbers. Further experiments are conducted to visualize the overall flow structures over the test models by self-illumination of radicals at high-energy states post strong shock waves. The heat flux at the stagnation point is measured with specially designed thermal couples.

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 EPUB and PDF
  • Read on any device
  • Instant download
  • Own it forever
Hardcover Book
USD 379.99
Price excludes VAT (USA)
  • Durable hardcover edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

References

  1. R.G. Morgan, R.J. Stalker, Double diaphragm driven expansion tube, in Proceedings of the 18th International Symposium on Shock Waves, Sendai, Japan, 1991

    Google Scholar 

  2. M.P. Scott, Development and Modeling of Expansion Tubes. PhD Thesis, University of Queensland, St. Lucia, Australia, 2006

    Google Scholar 

  3. A. Sasoh, K. Ohnishi, K. Koremoto, K. Takayama, Operation design and performance of a free piston driven expansion tube, in 37th AIAA Aerospace Sciences Meting and Exhibition, Reno, Nevada, AIAA paper 99-0825, 1999

    Google Scholar 

  4. R.S.M. Chue, C.Y. Tsai, R.J. Bakos, J.I. Erdos, R.C. Rogers, NASA’s HYPULSE facility at GASL-A dual mode, dual driver reflected-shock/expansion tunnel, in Advanced Hypersonic Test Facilities, vol. 198, ed. by F. Lu, D. Marren (AIAA, 2002), pp. 29–71

    Google Scholar 

  5. M.S. Holden, T.P. Wadhams, M. MacLean, E. Mundy, Experimental studies in the LENS I and X to evaluate real gas effects on hypervelocity vehicle performance, in 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, AIAA paper 2007-204, 2007

    Google Scholar 

  6. Y.L. Gao, Study on Hypervelocity Flow Generation Techniques and Essential Hypersonic Phenomena. PhD Thesis, Institute of Mechanics, Beijing, China, 2008

    Google Scholar 

  7. B. Wu, Study on the Interaction of Strong Shock Wave and the Hypervelocity Experimental Method. PhD Thesis, Institute of Mechanics, Beijing, China, 2012

    Google Scholar 

  8. Z.L. Jiang, B. Wu, Y.L. Gao, W. Zhao, Z.M. Hu, Development of the detonation-driven expansion tube for orbital speed experiments. Sci. China Tech. Sci. 58(4), 695–700 (2015)

    Article  Google Scholar 

  9. H. Yu, B. Esser, M. Lenartz, H. Grönig, Gaseous detonation driver for a shock tunnel. Shock Waves 2, 245–254 (1992)

    Article  Google Scholar 

  10. Z. Jiang, W. Zhao, C. Wang, K. Takayama, Forward-running detonation drivers for high-enthalpy shock tunnels. AIAA J. 40, 2009–2016 (2002)

    Article  Google Scholar 

  11. Z.M. Hu, Z.L. Jiang, Numerical predictions for the hypervelocity test flow conditions of JF-16, in 29th International Symposium on Shock Waves, Madison, America, 2013

    Google Scholar 

  12. Z.M. Hu, Z.L. Jiang, Computer-aid diagnostic of hypersonic test flow in a shock-expansion tube, in The 9th Pacific Symposium on Flow Visualization and Image Processing, Bisan, South Korea, 2013

    Google Scholar 

  13. Z.M. Hu, C. Wang, Z.L. Jiang, B.C. Khoo, On the numerical technique for the simulation of hypervelocity test flows. Comput. Fluids 2015(106), 12–18 (2015)

    Article  MathSciNet  Google Scholar 

  14. K. Zhou, C.K. Yuan, Z. Hu, Z. Jiang, Test flow analysis and upgrade of JF-16 expansion tune. Acta. Aeronaut. et Astronaut. Sin. 37, 3296–3303 (2016)

    Google Scholar 

  15. K. Zhou, Experimental Study on Hypervelocity Flow with Expansion Tunnel. PhD Thesis, Institute of Mechanics, Beijing, China, 2017

    Google Scholar 

  16. M. MacLean, M. Holden, Numerical assessment of data in catalytic and transitional flows for Martian entry, AIAA 2006-2946 (2006)

    Google Scholar 

  17. M. MacLean, T. Wadhams, M. Holden, Integration of CFD and experiments in the CUBRC LENS shock tunnel facilities to understand the physics of hypersonic and hypervelocity flows, in 4th Symposium on Integrating CFD and Experiments in Aerodynamics, Rhode-Saint-Genese, Belgium, Set. 14–16, 2009

    Google Scholar 

  18. M. Sharma, A.B. Swantek, W. Flaherty, J.M. Austin, S. Doraiswamy, G.V. Candler, Evaluation of hypervelocity carbon dioxide blunt body experiments in an expansion tube facility, AIAA 2011-136 (2011)

    Google Scholar 

  19. F.D. Filippis, R. Savino, A. Martucci, Numerical-experimental correlation of stagnation point heat flux in high enthalpy hypersonic wind tunnel, AIAA Paper 2005-3277 (2005)

    Google Scholar 

Download references

Acknowledgments

This work was supported by the National Natural Science Foundation of China under Grant No. 11672308 and 11532014.

Author information

Authors and Affiliations

  1. State Key Laboratory of High-temperature Gas Dynamics, Institute of Mechanics, Beijing, China

    Z. Hu, K. Zhou, J. Peng & Z. Jiang

  2. School of Engineering Science, University of Chinese Academy of Sciences, Beijing, China

    Z. Hu, K. Zhou, J. Peng & Z. Jiang

Authors
  1. Z. Hu
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. K. Zhou
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. J. Peng
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Z. Jiang
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Z. Hu .

Editor information

Editors and Affiliations

  1. Department of Aerospace Engineering, Nagoya University, Nagoya, Japan

    Akihiro Sasoh

  2. Department of Energy and Environmental Engineering, Kyushu University, Kasuga, Fukuoka, Japan

    Toshiyuki Aoki

  3. Institute of Innovative Research, Tokyo Institute of Technology, Tokyo, Japan

    Masahide Katayama

Rights and permissions

Reprints and permissions

Copyright information

© 2019 Springer Nature Switzerland AG

About this paper

Check for updates. Verify currency and authenticity via CrossMark

Cite this paper

Hu, Z., Zhou, K., Peng, J., Jiang, Z. (2019). Hypervelocity Test with a Detonation-Driven Expansion Tube. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 2. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91017-8_32

Download citation

  • DOI: https://doi.org/10.1007/978-3-319-91017-8_32

  • Published:

  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-91016-1

  • Online ISBN: 978-3-319-91017-8

  • eBook Packages: EngineeringEngineering (R0)

Publish with us

Policies and ethics

Search

Navigation