SpringerLink
Log in

Investigation of the Flow Structure in a Model Scramjet Air Intake with Transverse Hydrogen Fuel Injection into Supersonic Crossflow

  • Published:
Fluid Dynamics Aims and scope Submit manuscript

Abstract—

Combustion flow inside the channel of a model scramjet air inlet with transverse hydrogen fuel injection from the bottom wall is investigated. The OH-concentration and pressure distributions that replicate qualitatively the flow structure observed in experiments are obtained. Several different mechanisms of formation of shock waves in the investigated experimental facility are distinguished. In analyzing the structure of fuel jet, satisfactory quantitative agreement with the calculation results of other authors is obtained. It is shown that the shock-wave structure affects significantly combustion enhancement.

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

Access this article

Log in via an institution

Subscribe and save

Springer+ Basic
EUR 32.99 /Month
  • Get 10 units per month
  • Download Article/Chapter or Ebook
  • 1 Unit = 1 Article or 1 Chapter
  • Cancel anytime
Subscribe now

Buy Now

Price includes VAT (Germany)

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1.
Fig. 2.
Fig. 3.
Fig. 4.
Fig. 5.
Fig. 6.
Fig. 7.

Similar content being viewed by others

REFERENCES

  1. Seleznev, R.K., Surzhikov S.T., and Shang, J.S., A review of the scramjet experimental data base, Progress in Aerospace Sciences, 2019, vol. 106, no. 2, pp. 43–70.

    Article  ADS  Google Scholar 

  2. Waltrup P.J., White, M.E., Zarlingo, F., and Gravlin, E.S., History of ramjet and scramjet propulsion development for U.S. Navy missiles, Johns Hopkins APL Technical Digest (Applied Physics Laboratory), 1997, vol. 18, no. 2, pp. 234–242.

    Google Scholar 

  3. Seleznev, R.K., History of scramjet propulsion development, Journal of Physics: Conf. Ser., 2018, vol. 1009, no. 1, p. 012028.

    Google Scholar 

  4. Gamba, M., Miller, V.A., Mungal, M.G., and Hanson, R.K., Ignition and lame structure in a compact inlet/scramjet combustor model, AIAA 2011-2366.

  5. Zhao, M., Zhou, T., Ye, T., Zhu, M., and Zhang, H., Large eddy simulation of reacting flow in a hydrogen jet into supersonic cross-flow combustor with an inlet compression ramp, International Journal of Hydrogen Energy, 2017, vol. 42, no. 26, pp. 16782–16792.

    Article  Google Scholar 

  6. Seleznev, R.K., Validation of 3D model by the example of a supersonic inlet-isolator, Journal of Physics: Conf. Ser., 2018, vol. 1009, p. 012031.

    Google Scholar 

  7. Zhao, M., Zhou, T., Ye, T., Zhu, M., and Cao, C., Study of sonic injection from circular injector into a supersonic cross-flow using large eddy simulation, International Journal of Hydrogen Energy, 2016, vol. 41, no. 39, pp. 17657–17669.

    Article  Google Scholar 

  8. Gamba, M. and Mungal, M.G., Ignition, flame structure and near-wall burning in transverse hydrogen jets in supersonic crossflow, Journal of Fluid Mechanics, 2015, vol. 780, pp. 226–273.

    Article  ADS  MathSciNet  Google Scholar 

  9. Ben-Yakar, A., Mungal, M.G., and Hanson, R.K., Time evolution and mixing characteristics of hydrogen and ethylene transverse jets in supersonic crossflows, Physics of Fluids, 2006, vol. 18, no. 2, p. 026101.

    Article  ADS  Google Scholar 

  10. Bird, R., Stewart, V., and Lightfoot, E., Transport Phenomena, New York: Wiley, 1960.

    Google Scholar 

  11. Anfimov, N.A., Laminar boundary layer in a multicomponent gas mixture, Izv. Akad. Nauk SSSR, Mekhanika i Mashinostroenie, 1962, no. 1, pp. 25–31.

  12. Edwards, J.R. and Liou, M.-S., Low-diffusion flux-splitting methods for flow at all speeds, AIAA J., 1998, vol. 36, no. 9, pp. 1610–1617.

    Article  ADS  Google Scholar 

  13. Evans, J.S. and Schexnayder, C.J., Influence of chemical kinetics and unmixedness on burning in supersonic hydrogen flames, AIAA J., 1980, vol. 18, no. 2, pp. 188–193.

    Article  ADS  Google Scholar 

  14. Surzhikov, S.T., Three-dimensional problem of radiative gasdynamics of the Apollo-4 command module during superorbital atmospheric entry, Fluid Dynamics, 2018, vol. 53, no. 2, pp. 325–336. https://doi.org/10.1134/S0015462818020155

    Article  ADS  MathSciNet  MATH  Google Scholar 

  15. Surzhikov, S.T., Simulation of radiative-convective heating of ramjet model chambers on hydrogen and hydrocarbon fuel, Fiziko-Khimicheskaya Kinetika v Gazovoi Dinamike, 2014, vol. 15, no. 3. http://chemphys.edu.ru/issues/2014-15-3/articles/230/.

  16. Surzhikov, S.T., Seleznev, R.K., Tretyakov, P.K., and Zabaykin, V.A., Unsteady thermo-gasdynamic processes in scramjet combustion chamber with periodical input of cold air, AIAA 2014-3917.

Download references

ACKNOWLEDGEMENTS

The author wishes to thank S.T. Surzhikov and V.V. Kuznetsov for fruitful discussions and useful remarks.

Author information

Authors and Affiliations

  1. Dukhov Automatics Research Institute, Moscow, Russia

    R. K. Seleznev

  2. Ishlinsky Institute for Problems in Mechanics of the Russian Academy of Sciences, Moscow, Russia

    R. K. Seleznev

  3. The Moscow Institute of Physics and Technology (National Research University), Dolgoprudnyi, Moscow Region, Russia

    R. K. Seleznev

Authors
  1. R. K. Seleznev
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to R. K. Seleznev.

Additional information

Translated by E.A. Pushkar

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Seleznev, R.K. Investigation of the Flow Structure in a Model Scramjet Air Intake with Transverse Hydrogen Fuel Injection into Supersonic Crossflow. Fluid Dyn 56, 334–342 (2021). https://doi.org/10.1134/S0015462821030083

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1134/S0015462821030083

Keywords:

Search

Navigation