Applied Mathematics and Mechanics

, Volume 22, Issue 4, pp 460–467 | Cite as

Study on the Fuel Air Mixing Induced by a Shock Wave Propagating into a H2-Air Interface

  • Sheng-li Xu
  • Peng-tao Yue
  • Zhao-yuan Han


2nd-order upwind TVD scheme was used to solve the laminar, fully Navier-Stokes equations. The numerical simulations were done on the propagation of a shock wave with MaS = 2 and 4 into a hydrogen and air mixture in a duct and a duct with a rearward step. The results indicate that a swirling vortex may be generated in the lopsided interface behind the moving shock. Meanwhile, the complex shock system is also formed in this shear flow region. A large swirling vortex is produced and the fuel mixing can be enhanced by a shock wave at low Mach number. But in a duct with a rearward step, the shock almost disappears in hydrogen for MaS = 2. The shock in hydrogen will become strong if MaSis large. Similar to the condition of a shock moving in a duct full of hydrogen and air, a large vortex can be formed in the shear flow region. The large swirling vortex even gets through the reflected shock and impacts on the lower wall. Then, the distribution of hydrogen behind the rearward step is divided into two regions. The transition from regular reflection to Mach reflection was observed as well in case MaS = 4.

shock wave swirling vortex shear layer fuel mixing numerical simulation 


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. [1]
    Drummond J P, Hussaini. Numerical simulation of a supersonic reacting mixing layer[A]. AIAA Paper, 87-1325,1987.Google Scholar
  2. [2]
    Roshko A. Structure of the turbulent shear flow: New Look[J]. AIAA J,1976,14(10):1349.Google Scholar
  3. [3]
    Guiguis R H, Grinstein F F, Young T R, et al. Mixing enhancement in supersonic shear layers[A] AIAA Paper, 87-0373,1987.Google Scholar
  4. [4]
    LIU Jun. GAO Shu-chun. Numerical study on supersonic free shear layers[J]. Acta Aerodynamica Sinica, 1995,13(2):152-158. (in Chinese)Google Scholar
  5. [5]
    Yee H C, Klopeer G H, Montagne J L. High-Resolution Shock-capturing schemes for inviscid and viscous hypersonic flows[J]. J Comput Phys,1990,88:31-61.Google Scholar
  6. [6]
    Gordon S, McBride D J. Computer program for a calculation of complex chemical equilibrium compositions, rockets performance, incident and reflected shocks, Chapman-Joudguet detonations[A]. NASA SP-273,1971.Google Scholar
  7. [7]
    Eklund D R, Stouffer S D. A numerical and experimental study of a supersonic combustor employing swept ramp fuel injectors[A]. AIAA Paper 94-2819,1994.Google Scholar

Copyright information

© Kluwer Academic Publishers 2001

Authors and Affiliations

  • Sheng-li Xu
    • 1
  • Peng-tao Yue
    • 1
  • Zhao-yuan Han
    • 1
  1. 1.Department of Modern MechanicsUniversity of Science and Technology of ChinaHefeiP R China

Personalised recommendations