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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1993, Vol. 14 ›› Issue (1): 14-19.

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NUMERICAL STUDY OF SUPERSONIC FLOW OVER A BACKWARD STEP WITH TRANSVERSE INJECTION

Zhou Wei-jiang1, Ma Han-dong1, Ma Yan-wen2   

  1. 1. Beijing Institute of Aerodynamic.s, Beijing, 100074;2. institute of Mechanics Academia Sinica, Bijing, 100080
  • Received:1991-12-02 Revised:1992-06-20 Online:1993-01-25 Published:1993-01-25

Abstract: The interaction between a supersonic flow around a backward step and transverse injectors (Ma, = 1.05) located on the downstream of the step is simulated with finite difference method by solving the N-S equations numerically. Firsi. the supersonic flows over a backward step without an injecter are computed, and the results are compared with the experiment and other calculations. Then the injector is added, with the pressure ratio pj/p∞ varying from 3.033 to 7.033 and the injector width w equal to 0.1h or 0.2h(h-step height). The reasonable structures of vortes and waves are presented, and the effects of pj/p∞ and w on flow properties are researched. Within the present parameters region, the calculations also show that the pressure at the step bottom is almost linearly related to the factor Q(Q = wpj/hp∞).

Key words: jet, numerical simulation. N-S equations. separation flow