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NTIS 바로가기한국추진공학회지 = Journal of the Korean Society of Propulsion Engineers, v.22 no.6, 2018년, pp.72 - 83
정승민 (Department of Aerospace Engineering, Pusan National University) , 엄재령 (Satellite System Team, Korea Aerospace Industries LTD) , 최정열 (Department of Aerospace Engineering, Pusan National University)
In this study, a series of CFD analyses were carried out for a hydrogen rocket combustor with a single shear coaxial injector. A hybrid RANS/LES approach was used for the turbulent combustion analysis with a two-dimensional axisymmetric configuration. Three reaction mechanisms, three spatial discret...
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핵심어 | 질문 | 논문에서 추출한 답변 |
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우주선진국들이 각국의 주력 우주발사체에 수소엔진을 상단 엔진으로 이용하고 있는 이유는? | 액체수소의 높은 비추력은 극저온에 따른 기술적 어려움과, 낮은 밀도에 따른 구조비의 증가를 상쇄하고도 수송능력을 크게 증가시킬 수 있는 최상의 추진제이다. 따라서 모든 우주선진국은 오래전부터 액체수소 엔진을 개발하기 위하여 노력하여 왔으며, 현재 각국의 주력 우주발사체들은 수소엔진을 상단 엔진으로 이용하고 있다. | |
열전달 계수는 어떻게 정의되는가? | 열전달 계수는 층류 및 난류 열전달 계수의 합으로 정의되며, 연소 된 혼합 기체의 층류 열전달 계수는 Wilke의 혼합법칙을 통해 계산되고 난류 열전달 계수는 난류 Prandtl 수를 0.9 로가정[14]하여 난류 점성 계수로부터 계산된다. | |
로켓 연소기에 나타나는 현상은? | 로켓 연소기는 큰 유량의 산화제 및 연료가 일으키는 연소현상으로 인해 고온의 난류연소 유동장이 형성된다. 이 유동장의 특징을 측정하기란 매우 힘들다. |
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