Effects of Supersonic Nozzle Geometry on Characteristics of Shock Wave Structure

Shigeru Matsuo, Kousuke Kanesaki, Junji Nagao, Md. Tawhidul Islam Khan, Toshiaki Setoguchi, Heuy Dong Kim

Department of Advanced Technology Fusion, Saga University, Saga Japan.
Graduate School of Science & Engineering, Saga University, Saga, Japan.
Institute of Ocean Energy, Saga University, Saga, Japan.
School of Mechanical Engineering, Andong National University, Andong, Korea.

DOI: 10.4236/ojfd.2012.24A019                

Abstract

Interaction between the normal shock wave and the turbulent boundary layer in a supersonic nozzle becomes complex with an increase of a Mach number just before the shock wave. When the shock wave is strong enough to separate the boundary layer, the shock wave is bifurcated, and the 2nd and 3rd shock waves are formed downstream of the shock wave. The effect of a series of shock waves thus formed, called shock train, is considered to be similar to the effect of one normal shock wave, and the shock train is called pseudo-shock wave. There are many researches on the configuration of the shock wave. However, so far, very few researches have been done on the asymmetric characteristics of the leading shock wave in supersonic nozzles. In the present study, the effect of nozzle geometry on asymmetric shock wave in supersonic nozzles has been investigated experimentally.

Keywords

Compressible Flow; Asymmetric Shock Wave; Supersonic Nozzle; Experiment

Conflicts of Interest

The authors declare no conflicts of interest.

References

[1]	K. Matsuo, Y. Miyazato and H. D. Kim, “Shock Train and Pseudo-Shock Phenomena in Internal Gas Flows,” Progress in Aerospace Sciences, Vol. 35, No. 1, 1999, pp. 33-100. doi:10.1016/S0376-0421(98)00011-6
[2]	E. P. Neumann and F. Lustwerk, “Supersonic Diffusers for Wind Tunnels,” Journal of Applied Mechanics, Vol. 16, No. 2, 1949, pp. 195-202.
[3]	T. Tamaki, Y. Tomita and R. Yamane, “A Research on Pseudo-Shock (1st Report, λ-Type Pseudo-Shock),” Bulletin of JSME, Vol. 13, No. 55, 1970, pp. 191-226.
[4]	T. Tamaki, Y. Tomita and R. Yamane, “A Research on Pseudo-Shock (2nd Report, X-Type Pseudo-Shock),” Bulletin of JSME, Vol. 14, No. 74, 1971, pp. 807-817.
[5]	Q. Xiao, H. M. Tsai and D. Papamoschou, “Numerical Investigation of Supersonic Nozzle Flow Separation,” AIAA Journal, Vol. 45, No. 3, 2007, pp. 532-541. doi:10.2514/1.20073
[6]	D. Papamoschou and A. Zill, “Fundamental Investigation of Supersonic Nozzle Flow Separation,” American Institute of Aeronautics and Astronautics, Inc., Reston, 2004.
[7]	D. Papamoschou, A. Zill and A. Johnson, “Supersonic Flow Separation in Planar Nozzles,” Shock Waves, Vol. 19, No. 3, 2006, pp. 171-183. doi:10.1007/s00193-008-0160-z
[8]	D. Papamoschou and A. Johnson, “Unsteady Phenomena in Supersonic Nozzle Flow Separation,” American Institute of Aeronautics and Astronautics, Inc., Reston, 2006.
[9]	J. M. Weiss and W. A. Smith, “Preconditioning Applied to Variable and Constant Density Flows,” AIAA Journal, Vol. 33, No. 11, 1995, pp. 2050-2057. doi:10.2514/3.12946
[10]	F. R. Menter, “Zonal Two Equation k-ω Turbulence Models for Aerodynamic Flows,” American Institute of Aeronautics and Astronautics, Inc., Reston, 1993.
[11]	F. R. Menter, “Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications,” AIAA Journal, Vol. 32, No. 8, 1994, pp. 269-289. doi:10.2514/3.12149
[12]	F. R. Menter, M. Kuntz and R. Langtry, “Ten Years of Industrial Experience with the SST Turbulence Model,” Proceedings of the 4th International Symposium on Turbulence, Heat and Mass Transfer, Begell House Inc., West Redding, 2003, pp. 625-632.