Numerical Analysis of Scramjet Internal Flow by Hybrid Unstructured Grid Method

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Author(s)

Abstract

Computations of internal viscous flowfields of scramjet models were conducted at inflow Mach numbers of 3.4 and 5.45. A hybrid unstructured grid method was used to compute the scramjet models with and without a short strut. The numerical method to solve the Navier-Stokes equations on the hybrid unstructured grid was developed using a finite volume cell vertex scheme and the lower-upper symmetric Gauss-Seidel (LU-SGS) implicit time integration algorithm. The computational results revealed that a thick subsonic region did not exist in the combustor near the top wall at Mach number 5.45. It was a desirable feature to avoid unstarting the engine. With the use of a strut, the relatively low velocity regions increased and the downward flow toward the cowl behind the step became strong. An overconcentration of fuel toward the top wall during weak combustion was observed in the experiment. The reason for this was that the airflow near the injector was turned to the top wall due to the small influence of combustion in the experiment.

Journal

  • JSME International Journal Ser. B Fluids and Thermal Engineering

    JSME International Journal Ser. B Fluids and Thermal Engineering 43(3), 407-413, 2000-08-15

    The Japan Society of Mechanical Engineers

References:  13

Codes

  • NII Article ID (NAID)
    110003474357
  • NII NACSIS-CAT ID (NCID)
    AA10888815
  • Text Lang
    ENG
  • Article Type
    ART
  • ISSN
    13408054
  • NDL Article ID
    5439288
  • NDL Source Classification
    ZN11(科学技術--機械工学・工業)
  • NDL Call No.
    Z53-Y271
  • Data Source
    CJP  NDL  NII-ELS 
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