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학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
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연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2018.5
- 수록면
- 568 - 573 (6page)
이용수
이 논문의 연구 히스토리 (9)
2020
Performance Assessment of the Dual-Throat Nozzle Thrust Vector Control in a 3D Rectangular Nozzle
Kexin Wu
,
Tae Ho Kim
,
Heuy Dong Kim
한국추진공학회지
2020.08
학술저널
Assessment of the Counter-Flow Thrust Vector Control in a Three-Dimensional Rectangular Nozzle
Kexin Wu
,
Tae Ho Kim
,
James Jintu Kochupulickal
외 1명
한국추진공학회지
2020.02
학술저널
2019
Performance Assessment of the Dual-Throat Nozzle Thrust Vector Control in a 3D Rectangular Nozzle
Kexin Wu
,
Tae Ho Kim
,
Heuy Dong Kim
한국추진공학회 학술대회논문집
2019.11
학술대회자료
Fluidic Thrust Vector Control Using Shock Wave Concept
Kexin Wu
,
Heuy Dong Kim
한국추진공학회지
2019.08
학술저널
Assessment of the Counter-Flow Thrust Vector Control in a 3D Rectangular Nozzle
Kexin Wu
,
Heuy Dong Kim
한국추진공학회 학술대회논문집
2019.05
학술대회자료
Study on Fluidic Thrust Vector Control Based on Dual-Throat Concept
Kexin Wu
,
Heuy Dong Kim
한국추진공학회지
2019.02
학술저널
- 이 논문의 후속연구가 궁금하신가요?
- 연관 학술논문 또는 학술발표를 통해 보다 발전된 연구결과를 확인하실 수 있습니다.
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초록· 키워드
오류제보하기
Numerical simulations are carried out on a supersonic nozzle to study the possibility of using dual-throat technique in fluidic thrust vector control. In the present work, the high efficiency and system resultant thrust ratio of the asymmetric dual-throat nozzle is illustrated. For the validation of methodology, CFD data are compared with experiment which is referred from the NASA Langley Research Center. 2D computational results are based on well-assessed SST k-ω turbulence model that it is recognized as the best in the compressible fluid dynamics. Second order accuracy is selected to reveal the details of the flow field as much as possible. The deflection angle, system resultant thrust ratio and thrust efficiency are investigated in a wide range of nozzle pressure ratios (NPRs) and injection pressure ratios (IPRs). Over-expanded and under-expanded flow conditions should be considered for corresponding to the different flight situations. Hence, it is decided to illustrate the performance variation with the changing of NPR values when the IPR is fixed at 7.6. The results report that deflection angle is decreasing with the increasing of NPR values. Meanwhile, the system resultant thrust ratio is found to be increased with the increasing of NPR as well as the thrust efficiency. As the NPR is set to 4, the deflection angle increases rapidly when IPR is less than 7. Then it follows by a smooth and slow increasing with the increase of IPRs. The system resultant thrust ratio is remained decreasing trend with the increasing of IPR value. The highest thrust efficiency is obtained at IPR=3.
목차
ABSTRACT
1. Introduction
2. Computational domain
3. Results and discussions
4. Conclusion
References
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