한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제40권5호
  • /
  • Pages.375-384
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  • 2012
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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초음속 유동 해석을 위한 Wilcox к - ω 난류 모델 비교

Comparison between Wilcox к - ω turbulence models for supersonic flows

  • 김민하 (부산대학교 항공우주공학과 대학원) ;
  • 투고 : 2011.12.02
  • 심사 : 2012.04.06
  • 발행 : 2012.05.01
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초록

본 연구에서는 초음속 비행체에 나타나는 유동 특성 해석을 위해 1988 Wilcox $\mathcal{k}-{\omega}$ 모델과 2008 Wilcox 모델의 수치 결과를 비교하였다. 충격파 - 경계층 간섭 현상과 램프 주입기 혼합 문제에 대하여 실험결과와 비교, 검토하였다. 또한, 표면 마찰 측정의 기초가 되는 평판 흐름과 전단 층 성장에 대한 상관 관계식도 비교, 분석 하였다. 램프 주입기 케이스에서 최대 주입 질량비는 1988 Wilcox 모델을 이용하였을 때 보다 신뢰성 있는 해석 결과를 예측할 수 있었다. 그러나 충격파 - 경계층 간섭 케이스에 대해서는 2008 Wilcox 모델을 적용하였을 때 더 정확한 해석 결과가 도출됨을 확인하였다.

This paper presents numerical results comparing the performance of the 2008 Wilcox $\mathcal{k}-{\omega}$ turbulence model to the one of the 1988 Wilcox $\mathcal{k}-{\omega}$ model for supersonic flows. A comparison with experimental data is offered for a shock wave/turbulent boundary layer interaction case and two ramp injector mixing cases. Furthermore, a comparison is performed with empirical correlations on the basis of skin friction for flow over a flat plate and shear layer growth for a free shear layer. It is found that the maximum injectant mass fraction of some ramp injector cases is better predicted using the 1988 Wilcox model. On the other hand, the 2008 model performs better in simulating shock-boundary layer cases.

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참고문헌

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