Three-Dimensional Mixing Flow Field in Supersonic Flow Induced by Injected Secondary Flow through a Traverse Circular Nozzle

  • Shigeru Aso
  • Shozo Maekawa
  • Michiaki Tan-Nou
  • Satosh Okuyama
  • Yasunori Ando
  • Yoshiyuki Yamane
Conference paper

Abstract

Shock wave/turbulent boundary layer interaction regions induced by gaseous secondary flows injected into supersonic flows through circular nozzles have been experimentally and computationally investigated.

In the experiments the flowfields are visualized by the Schlieren method, oil flow technique, surface pressure; spatial total pressure distributions are measured in the whole interaction region. The total pressure ratio, P c /Po, (P c - total pressure of injected secondary flow, P0: total pressure of freestream) are varied and the changes of the flowfleld are investigated for circular injection. The detailed flow structures in three-dimensional mixing flow structures have been revealed. Especially, the surface oil patterns show a quite complicated flow in the interacting region with primary and secondary separations. Also, quite interesting Pitot pressure fields are revealed. The same flowflelds have been simulated by solving Navier-Stokes equations with turbulent modelling. Surface pressure and spatial Pitot pressure distributions show quite good agreement with experiments. The results suggest that the numerical code is quite useful for supersonic mixing flows.

Key words

Mixing flow SCRAM -jet engine Shock-boundary layer interaction 

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Copyright information

© Springer-Verlag Berlin Heidelberg 1995

Authors and Affiliations

  • Shigeru Aso
    • 1
  • Shozo Maekawa
    • 1
  • Michiaki Tan-Nou
    • 1
  • Satosh Okuyama
    • 1
  • Yasunori Ando
    • 2
  • Yoshiyuki Yamane
    • 2
  1. 1.Dept. Aeronautics and AstronauticsKyushu UniversityFukuoka 812Japan
  2. 2.Ishikawajima-Harima Heavy Industry, Co. LtdYokohama 235Japan

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