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D. Papamoschou and A. Johnson, “Unsteady Phenomena in Supersonic Nozzle Flow Separation,” American Institute of Aeronautics and Astronautics, Inc., Reston, 2006.

has been cited by the following article:

• TITLE: Effects of Supersonic Nozzle Geometry on Characteristics of Shock Wave Structure

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

  KEYWORDS: Compressible Flow; Asymmetric Shock Wave; Supersonic Nozzle; Experiment

  JOURNAL NAME: Open Journal of Fluid Dynamics, Vol.2 No.4A, December 26, 2012

  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.