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학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
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논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 저널정보
- 한국항공우주학회 한국항공우주학회 학술발표회 초록집 Proceedings of KSAS-JSASS Joint International Symposium on Aerospace Engineering
- 발행연도
- 2008.11
- 수록면
- 110 - 114 (5page)
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초록· 키워드
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In supersonic flight, an airplane generates shock waves that cause large wave drag as well as strong sonic boom. A supersonic airplane based on Busemann biplane was proposed as an innovative solution to realize supersonic transport. Shock waves are generated at the leading edge of the Busemann biplane and are cancelled by expansion waves generated from the ridgeline or the wings so that shock waves are confined inside the biplane and the drag and the sonic boom are dramatically reduced.
The objective of this study is to investigate the three-dimentional shock interactions of a Busemann biplane by experiment. A supersonic biplane model with the aspect ratio of 2.5 was tested in a blow-down supersonic wind tunnel at M<SUB>∞</SUB> = 1.5 to 1.7. Interacting flow around the wings was visualized by schlieren method and the pressure distribution on an inner surface of the wing was measured using pressure-sensitive paint (PSP). CFD calculations were also made to compare with experimental results. On the basis of these experimental and computational studies, the complicated three-dimensional interference phenomenon between the two wings, including shock wave/boundary layer interactions were analyzed and the three-dimensional flow effects on the start/uri start characteristics of the Busemann biplane are discussed.
The objective of this study is to investigate the three-dimentional shock interactions of a Busemann biplane by experiment. A supersonic biplane model with the aspect ratio of 2.5 was tested in a blow-down supersonic wind tunnel at M<SUB>∞</SUB> = 1.5 to 1.7. Interacting flow around the wings was visualized by schlieren method and the pressure distribution on an inner surface of the wing was measured using pressure-sensitive paint (PSP). CFD calculations were also made to compare with experimental results. On the basis of these experimental and computational studies, the complicated three-dimensional interference phenomenon between the two wings, including shock wave/boundary layer interactions were analyzed and the three-dimensional flow effects on the start/uri start characteristics of the Busemann biplane are discussed.
목차
Abstract
1. Introduction
2. Start/unstart condition of supersonic biplane
3. Supersonic wind tunnel testing
4. Results and discussions
5. Conclusions
ACKNOWLEDGEMENTS
REFERENCES
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