한국전산유체공학회지 (Journal of computational fluids engineering)

한국전산유체공학회 (Korean Society of Computational Fluids Engineering)
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CFD를 이용한 유도탄 power-on 기저항력 해석

NUMERICAL SIMULATION OF THE POWER-ON BASE DRAG OF A MISSILE BODY

  • 최재혁 (국방과학연구소 제 1기술연구본부) ;
  • 이은석 (국방과학연구소 제 1기술연구본부) ;
  • 이광섭 (국방과학연구소 제 1기술연구본부)
  • Choi, J.H. (R&D Institute-1, Agency for Defense Development) ;
  • Lee, E.S. (R&D Institute-1, Agency for Defense Development) ;
  • Lee, K.S. (R&D Institute-1, Agency for Defense Development)
  • 투고 : 2014.11.21
  • 심사 : 2015.05.08
  • 발행 : 2015.06.30
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초록

The pressure is generally lower than that of the freestream at the base of a missile body due to the energy loss by the flow separation around the edge of the base. The base pressure changes in the presence of the thrust jet due to the interaction between the base flow of the missile and the jet flow. In this study, behavior of the missile base pressure by the change of the jet exit pressure and the freestream condition is investigated using the CFD(Computational Fluid Dynamics) method. Effects of the grid type and the freestream condition are tested. The results are compared with the semi-empirical predictions and the flight test data. The CFD results agree well with the flight test data. The semi-empirical predictions overestimate the base pressure when jet thrust is strong for low freestream speed.

키워드

참고문헌

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피인용 문헌

  1. 초음속 유동에서 챔버 압력에 따른 기저항력 변화 예측 vol.48, pp.11, 2015, https://doi.org/10.5139/jksas.2020.48.11.849