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

  • 제40권12호
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  • Pages.1025-1031
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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 흡입구 개념 설계와 운영조건 내의 블리딩(bleeding) 유동제어 연구

Study on Concept Design of Supersonic Inlet and Flow Control of Bleeding under Operating Condition

  • Choi, Jaehwan (Department of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Cheon, Somin (Department of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Choe, Yohan (Department of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Hong, Wooram (Interdisciplinary Program in Computational Science and Technology, Seoul National University) ;
  • Kim, Chongam (Department of Mechanical and Aerospace Engineering, Seoul National University)
  • 투고 : 2012.09.12
  • 심사 : 2012.11.29
  • 발행 : 2012.12.01
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초록

본 연구에서는 간단한 압축성 유체이론에 기초하여 렘젯 엔진의 초음속 흡입구를 개념 설계하고 보다 넓은 범위의 운영조건에서 안정적인 성능을 내도록 블리딩 유동제어 연구를 수행하였다. 초음속 흡입구의 성능을 개선시키기 위해서는 충격파 안정성, 충격파-경계층 상호작용 및 유동 박리를 적절히 제어할 수 있어야 한다. 비점성 해석을 통해 얻어진 1차 기초설계 형상으로부터 점성을 고려하여 충격파의 강도와 경계층 및 박리의 효과가 반영된 2차 수정설계를 수행하였다. 그 결과 설계조건에서 충격파가 안정화되고 목표 흡입 유량을 만족하는 형상을 얻었다. 흡입구가 탈 설계조건 내에서도 성능이 유지되도록 하기 위해 블리딩을 적용하였다. 질량유량 경계조건을 이용하여 블리딩 효과를 모델링 하였으며 위치와 개수를 조절해가며 성능변화를 관찰하였다.

The present paper deals with concept design of supersonic inlet based on compressible flow theory and flow control of bleeding in order to guarantee stability of supersonic inlet of ramjet engine in broad range of operating conditions. Shock instability, shock wave-boundary layer interaction and flow separation should be properly controlled to improve performance of the supersonic inlet. Considering shock strength, boundary layer and flow separation, the supersonic inlet is modified from the basic model which is designed under inviscid theory. Consequently, shock is stabilized, and required mass flow rate is obtained. Furthermore, bleeding is applied to the supersonic inlet to maintain performance in off-design conditions. Mass flow condition is adopted for modeling of bleeding effect, and performance of the supersonic inlet is evaluated by changing bleeding locations and numbers.

키워드

참고문헌

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