지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 저널정보
- 한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.13 Number.3
- 발행연도
- 2012.9
- 수록면
- 296 - 306 (11page)
이용수
초록· 키워드
오류제보하기
A series of numerical simulations are carried out to analyze a supersonic inlet buzz, which is an unsteady pressure oscillation phenomenon around a supersonic inlet. A simple but efficient geometry, experimentally adopted by Nagashima, is chosen for the analysis of unsteady flow physics. Among the two sets of simulations considered in this study, the effects of various throttling conditions are firstly examined. It is seen that the major physical characteristic of the inlet buzz can be obtained by inviscid computations only and the computed flow patterns inside and around the inlet are qualitatively consistent with the experimental observations. The dominant frequency of the inlet buzz increases as throttle area decreases, and the computed frequency is approximately 60Hz or 15% lower than the experimental data, but interestingly, this gap is constant for all the test cases and shock structures are similar. Secondly, inviscid calculations are performed to examine the effect regarding angle of attack. It is found that patterns of pressure oscillation histories and distortion due to asymmetric (or three-dimensional) shock structures are substantially affected by angle of attack. The dominant frequency of the inlet buzz, however, does not change noticeably even in regards to a wide range of angle of attacks.
목차
Abstract
1. Introduction
2. Numerical Method
3. Simulation Result
4. Conclusion
Acknowledgement
References
참고문헌 (21)
참고문헌 신청
Connors, J. F. / 1956 / Some Aspects of Supersonic Inlet Stability / NACA RM-E55L16a
Kwak, J.Y. / 2010 / Static Aeroelastic Analysis of a Supersonic Flight Vehicle with a Ramjet Engine / 51th AIAA/ASME/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Orlando, Florida
Oswatitsch, K. / 1947 / Pressure Recovery in Missiles with Reaction Propulsion at High Supersonic Speeds(the Efficiency of Shock Diffusers) / NACA TM-1140
Dailey, C. L. / 1955 / Supersonic Diffuser Instability / Journal of the Aeronautical Sciences 22(11):733~749
Ferri, A. / 1951 / The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions / NACA RM-L50K30
Kwak, J.Y. / 2010 / Static Aeroelastic Analysis of a Supersonic Flight Vehicle with a Ramjet Engine / 51th AIAA/ASME/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Orlando, Florida
Oswatitsch, K. / 1947 / Pressure Recovery in Missiles with Reaction Propulsion at High Supersonic Speeds(the Efficiency of Shock Diffusers) / NACA TM-1140
Dailey, C. L. / 1955 / Supersonic Diffuser Instability / Journal of the Aeronautical Sciences 22(11):733~749
Ferri, A. / 1951 / The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions / NACA RM-L50K30
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