Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Numerical Study of Shock Wave-Boundary Layer Interaction in a Curved Flow Path

굽어진 유로 내부의 충격파-경계층 상호작용 수치연구

  • Kim, Jae-Eun (Department of Aerospace Engineering, Pusan National University) ;
  • Jeong, Seung-Min (Department of Aerospace Engineering, Pusan National University) ;
  • Choi, Jeong-Yeol (Department of Aerospace Engineering, Pusan National University) ;
  • Hwang, Yoojun (Agency for Defense Development)
  • Received : 2020.12.24
  • Accepted : 2021.11.01
  • Published : 2021.12.31
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Abstract

Numerical analysis was performed on the shock wave-boundary layer interaction generated in the internal flow path of the curved interstage of the scramjet engine flight test vehicle. For numerical analysis, the turbulence model k-ω SST was used in the compressibility Raynolds Averaged Navier Stokes(RANS) equation. Representatively, the separation bubbles on the upper wall of the nozzle, the interaction between the concave shock wave and the boundary layer, and the shock wave-shock wave interaction at the edge were captured. The analysis result visualizes the shock wave-boundary layer interaction of the curved internal flow path to enhance understanding and suggest design considerations.

스크램제트 엔진 비행시험체의 굽어진 중앙동체 내부 유로에서 발생하는 충격파-경계층 상호작용에 대한 수치해석을 수행하였다. 수치해석에는 압축성 Raynolds Averaged Navier Stokes(RANS) 방정식에 난류모델 k-ω SST을 사용하였다. 대표적으로 노즐 윗 벽면의 박리기포, 오목한 충격파와 경계층의 상호작용, 모서리의 충격파-충격파 상호작용이 포착되었다. 해석 결과는 굽어진 내부 유로의 충격파-경계층 상호작용을 가시화하여 이해를 높이고 설계 유의점을 제시하였다.

Keywords

Acknowledgement

본 논문은 국방과학연구소의 재원으로 학술연구용역 지원사업(201903400001)의 지원으로 작성되었습니다.

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