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초음속 충돌 제트 운동에 대한 k-$\omega$ 난류모델의 적용
김유진,박수형,권장혁,김성인,박승오,이광섭,홍승규,Kim E.,Park S. H.,Kwon J. H.,Kim S. I.,Park S. O.,Lee K. S.,Hong S. G. 한국전산유체공학회 2004 한국전산유체공학회지 Vol.9 No.2
A numerical study of underexpanded jet and impingement on a wall mounted at various distances from the nozzle exit is presented. The 3-dimensional Wavier-Stokes equations and κ-ω turbulence equations are solved. The grids are constructed as overlapped grid systems to examine the distance effect. The DADI method is applied to obtain steady-state solutions. To avoid numerical instability such as the carbuncle phenomena that sometimes accompany approximate Riemann solver, the HLLE+ scheme is employed for the inviscid flux at the cell interfaces. A goal of this work is to apply a number of two-equation turbulence models based on the w equation to the impinging jet problem.
김유진(E. Kim),박수형(S. H. Park),권장혁(J. H. Kwon),김성인(S. I. Kim),박승오(S. O. Park),이광섭(K. S. Lee),홍승규(S. K. Hong) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
A numerical study of underexpanded jet and impingement on a wall mounted at various distances from the nozzle exit is presented. The 3-dimensional Navier-Stokes equations and k-ω turbulence equations are solved. The grids are constructed as overlapped grid systems to examine the distance effect. The DADI method is applied to obtain steady-state solutions. To avoid numerical instability such as the carbuncle that sometimes accompany approximate Riemann solver, the HLLE+ scheme is employed for the inviscid flux at the cell interfaces. A goal of this work is to apply a number of two-equation turbulence models based on the ω equation to the impinging jet problem.
김유진(E. Kim),박수형(S.H. Park),권장혁(J.H. Kwon),김성인(S.I. Kim),박승오(S.O. Park),이광섭(K.S. Lee),홍승규(S.K. Hong) 한국전산유체공학회 2004 한국전산유체공학회지 Vol.9 No.2
A numerical study of under expanded jet and impingement on a wall mounted at various distances from the nozzle exit is presented. The 3-dimensional Navier-Stokes equations and k-ω turbulence equations are solved. The grids are constructed as overlapped grid systems to examine the distance effect. The DADI method is applied to obtain steady-state solutions. To avoid numerical instability such as the carbuncle phenomena that sometimes accompany approximate Riemann solver, the HLLE+ scheme is employed for the inviscid flux at the cell interfaces. A goal of this work is to apply a number of two-equation turbulence models based on the ω equation to the impinging jet problem.
이남준 ( N. J. Yi ),한호성 ( H. S. Han ),김영우 ( Y. W. Kim ),민석기 ( S. K. Min ),김유진 ( E. G. Kim ),최용만 ( Y. M. Choi ),이선영 ( S. Y. Yi ),유권 ( K. Yu ),이한주 ( H. C. Lee ) 대한소화기학회 2002 대한소화기학회 춘계학술대회 Vol.2002 No.-
<목적> 간경변에 따른 위정맥류 출혈은 재출혈과 대량 출혈의 빈도가 높고 비관혈적 중재술이 어려워 수술적 치료를 요하는 경우가 많다. 따라서 빠른 수술 결정과 효과적인 수술 방법이 요구된다. 저자들은 수술 후 간 부전증의 빈도가 낮고 재출혈이 적은 새로운 방식의 비단락 술식을 적용하여, 유용성을 검증하고 수술 후 환자의 사망에 영향을 미치는 인자들을 분석하고자 하였다. <방법> 1994년 7월부터 2001년 7월까지 이대목동병원 외과에서 간경변에 따른
헬리콥터로부터 발사된 로켓의 초기 안정성에 대한 수치적 연구
이범석(B. S. Lee),김유진(K. T. Kang),강경태(E. J. Kim),권오준(O. J. Kwon) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.11
Numerical simulation of air-launched rockets from a helicopter was conducted to investigate the initial aerodynamic stability and its plume effect. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes and an mesh technique was used to describe the relative motion between missile launcher and launched rockets. The flow solver was coupled with six degree-of-freedom equation to predict the trajectory of free-flight rockets. Simulation of air-launched rockets from a helicopter showed that rotor downwash has non-negligible effect on the initial stability of the rockets and its plume development.
헬리콥터로부터 발사된 로켓의 공력 간섭 현상에 대한 수치적 연구
이범석(B.S. Lee),김유진(E.J. Kim),강경태(K.T. Kang),권오준(O.J. Kwon) 한국전산유체공학회 2011 한국전산유체공학회지 Vol.16 No.1
Numerical simulation of air-launched rockets from a helicopter was conducted to investigate the aerodynamic interference between air-launched rocket and helicopter. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes. An overset mesh technique was used to describe the relative motion between rocket and rocket launcher. The flow solver was coupled with six degree-of-freedom equation to predict the trajectory of free-flight rockets. For the validation, calculations were made for the impinging jet with inclined plate. The rotor downwash of helicopter was calculated and applied to simulation of air-launched rocket. It is shown that the rotor downwash has non-negligible effect on the air-launched rocket and its plume development.
중첩 격자 기법이 적용된 대각 내재적 조화균형법을 이용한 헬리콥터 로터 블레이드의 비정상 공력 해석
임동균(D. K. Im),최성임(S. I. Choi),김유진(E. Kim),권장혁(J. H. Kwon),박수형(S. H. Park) 한국전산유체공학회 2012 한국전산유체공학회지 Vol.17 No.1
In this paper, diagonal implicit harmonic balance method with overset grid technique is applied to analyze helicopter rotor blade flow in hover and forward flight condition. The chimera grid need interpolation time with sub-grid and background grid in moving problem such as forward flight on every time step. Present method is available enough to reduce the grid module interpolation time. In order to demonstrate present method, Caradonna & Tungs and AH-1G rotor blades are used and the results are compared to other researchers’ result and experimental data.