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표면열전달과 항력을 고려한 극초음속 비행체 선두부 최적형상설계
임설(S. Lim),서정일(J. I. Seo),송동주(D. J. Song) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
A design optimization of Sphere-Cone blunt nose hypersonic flight vehicle has been studied by using upwind Navier-Stokes method and numerical optimization method. Heat transfer coefficient and drag coefficient are selected as objective function or design constraint. Control points of Bezier curve are considered as design variable.
임설(S. Lim),전영진(Y. J. Jeon),조승환(S.H. Cho) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
The aerodynamic characteristics of the L-type side jet thruster are examined by using computational fluid dynamics methods. The critical design points of L-type side jet thruster with bent nozzle by 90degrees are studied in terms of the relation between side jet nozzle geometry and thrust efficiency.
안전성 평가를 위한 고체모터 노즐의 열, 유체-구조 연계해석
임설(S. Lim),김경식(K.S. Kim),김동우(D.W. Kim),조승환(S.W. Jo) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
In this study, Thermal fluid flow structural coupled analysis methods are studied to estimate thermal and structural safety of solid motor nozzle. Heat transfer rates and distributed surface pressure at the nozzle surface are estimated by using computational fluid dynamics methods. And standard type solid motor metal nozzles are tested to analyse thermal and structural characteristics.
Tangent-Ogive-Cylinder 비행체의 고앙각에서의 비대칭 와류 특성 연구
임설(S. Lim),김상덕(S. D. Kim),송동주(D. J. Song) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
The characteristics of asymmetric vortex and side force of tangent-ogive-cylinder flight vehicle at high angles of attack have been performed by using upwind Navier-Stokes method with the k-ω: turbulence model. And Asymmetric transition positions are considered for generation of asymmetric vortex.
표면 열전달율과 항력을 최소화한 극초음속 비행체 선두부 형상 최적설계
임설(S. Lim),서정일(J. I. Seo),김상덕(S. D. Kim),송동주(D. J. Song) 한국전산유체공학회 2005 한국전산유체공학회지 Vol.10 No.3
A design optimization of hypersonic flight vehicle has been studied by using upwind Navier-Stokes method and numerical optimization method. CFD method is linked to numerical optimization method by using a Bezier curve and a design optimization of blunt nose hypersonic flight vehicle has been studied. Heat transfer coefficient and drag coefficient are selected as objective functions or design constraints. The Bezier curve-based shape function was applied to blunt body shape.
치과 치료기기용 에어 모터 핸드피스의 성능에 관한 수치 해석적 연구
성용준(Y.J. Sung),임설(S. Lim),송동주(D.J. Song) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
Imported vane type air motor hand-piece is used widely in the domestic dental services. The imported hand-pieces are more than 90 percent in the domestic market. The air-motor unit of the hand-piece had not been developed inside of the country yet. Therefore it needs some research works. Purpose of this study is to design the air motor of the hand-piece for better performance. The geometry of the air-motor is based on product of NSK Company. The airflow of the air motor unit is simulated by Computational Fluid Dynamics. The performance analysis of the air motor units is investigated. ANSYS 12.0 CFX is used to analysis of the flowfield. Torque changes depends on rotor spin calculated by the immersed solid method.
박현호(H.H. Park),임설(S. Lim),백기봉(K.B. Baek),장선용(S.Y. Chang),조승환(S.H. Cho) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
The Performance analysis of the shutter valve for a thruster is examined by using numerical method. The initial design of shutter shows not enough performance of thrust and shutter torque that are caused high pressure drop near the supersonic nozzle throat. 3 cases of modified shutter design are proposed. Numerical calculation results of these cases are studied in terms of the relation between shutter shape, thrust efficiency and shutter torque.
초음속 흡입구의 통로길이와 받음각에 따른 유동장 변화 연구
류경진(K.J. Ryu),임설(S. Lim),김상덕(S.D. Kim),송동주(D.J. Song) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
The flow characteristics on a supersonic inlet with bleeding system by changing angles of attack and channel length conditions are studied by computational 3D turbulent flow analysis. A compressible upwind flux difference splitting Navier-Stokes method with k-ω turbulence model is used to analysis the inlet flowfield. More non-uniform flowfields are shown at the AIP when angle of attack becomes bigger and bigger. These non-uniform flowfield works the performance aggravating factors of the supersonic engine. Non-uniform flowfield by changing channel length at the various angle of attack are investigated.