Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Assessment of Turbulence Models with Compressibility Correction for Large Flow Separation in a Supersonic Convergent-Divergent Rectangular Nozzle

강한 박리 유동을 동반한 초음속 수축-확장 사각 노즐 유동에 적합한 난류 모델과 압축성 보정 모델의 평가

  • Lee, Juyong (Department of Aerospace Engineering, Korea Aerospace University) ;
  • Shin, Junsu (Department of Aerospace Engineering, Korea Aerospace University) ;
  • Sung, Hong-Gye (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • 이주용 (한국항공대학교 항공우주 및 기계공학과) ;
  • 신준수 (한국항공대학교 항공우주 및 기계공학과) ;
  • 성홍계 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2018.07.27
  • Accepted : 2018.10.14
  • Published : 2018.10.31
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Abstract

The objective of this study is to investigate the turbulence models with compressibility correction for large separation-flow in a supersonic convergent-divergent rectangular nozzle. As turbulence models, Yang and Shih's Low-Re $k-{\varepsilon}$ model, Mener's $k-{\omega}$ SST model and Wilcox's $k-{\omega}$model were evaluated. In order to get a significant compressible effects, Sarkar and Wilcox compressibility correction models were applied to the turbulence models respectively. Also, the simulation results were compared with experimental data. The turbulence model with compressibility correction model improves both of shock position and pressure recovery, but deteriorates the length of Mach disk.

초음속 수축-확대 사각 노즐 내 강한 유동 박리를 동반한 초음속 유동에 적합한 난류 모델과 압축성 보정 모델을 평가하였다. 난류 모델로는 Yang과 Shih의 Low-Re $k-{\varepsilon}$ 모델, Menter의 $k-{\omega}$ SST모델, Wilcox의 $k-{\omega}$ 모델을 평가하였다. 압축성 효과를 보다 정확하게 예측하기 위하여 각각의 난류 모델에 Sarkar와 Wilcox의 압축성 보정 모델을 적용하였다. 각 난류 모델과 압축성 보정 모델의 결과는 실험 데이터와 비교하여 분석을 하였다. 난류 모델에 따라 충격파의 위치와 압력 회복률이 다르게 나타났으나 압축성 보정을 통해 더욱 개선된 결과를 얻었다.

Keywords

References

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