Numerical Analysis of Detonation Wave Propagation in SCRam-Accelerator

초음속 연소 탄체 가속기 내의 폭굉파 진행에 관한 수치해석

  • 최정열 (서울대학교 항공우주공학과) ;
  • 정인석 (서울대학교 항공우주공학과) ;
  • 이수갑 (서울대학교 항공우주공학과)
  • Published : 1996.07.31

Abstract

A numerical study is carried out to examine the ignition and propagation process of detonation wave in SCRam-accelerator operating in superdetonative mode. The time accurate solution of Reynolds averaged Navier-Stokes equations for chemically reacting flow is obtained by using the fully implicit numerical method and the higher order upwind scheme. As a result, it is clarified that the ignition process has its origin to the hot temperature region caused by shock-boundary layer interaction at the shoulder of projectile. After the ignition, the oblique detonation wave is generated and propagates toward the inlet while constructing complex shock-shock interaction and shock-boundary layer interaction. Finally, a standing oblique detonation wave is formed at the conical ramp.

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