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이대성,신재렬,최정열,최윤수,김형원,Lee, D.S.,Shin, J.R.,Choi, J.Y.,Choi, Y.S.,Kim, H.W. 한국군사과학기술학회 2010 한국군사과학기술학회지 Vol.13 No.3
In this paper, the ionization characteristics of noble gases are studied numerically behind strong shock waves. As a first step, the equilibrium ionization mechanism of noble gases is modeled in wide ranges of temperature and pressure. As a next step the equilibrium ionization model is coupled with fluid dynamic equations to analyze the local thermodynamic equilibrium(LTE) ionization process at high temperature and pressure conditions behind the strong imploding shock waves. The ionization characteristics of xenon gas is studied in a wide range of test conditions with thermal radiation effects. Hence, the results give optimal conditions of maximum ionization and radiation behind the imploding shock waves.
비장착 엔진/나셀 형상에 대한 3차원 Euler 유동 해석
김수미(S.M. Kim),손창민(C.M. Son),양수석(S.S. Yang),이대성(D.S. Lee) 한국전산유체공학회 1996 한국전산유체공학회 학술대회논문집 Vol.1996 No.-
A reliable computational solver has been developed for the analysis of three-dimensional inviscid compressible flows around a nacelle of a high bypass ratio turbofan engine. The numerical algorithm is based on Godunov modified scheme to allow second order accuracy for space variables, while keeping the monotone features. Two step time integration is used not only to remove time step limitation but also to provide second order accuracy in a time variable. The multi-block approach is employed to calculate the complex flow field, using an algebraic grid solver, conformal grid solver, and elliptic grid solver. The exact solution of Riemann problem is used to define boundary conditions. The accuracy of the present method is validated by comparing its results for flows around the isolated nacelle in the cruise flight regime with the solution obtained using a commercial code "Rampant."
비장착 엔진/나셀 형상에 대한 3차원 Euler 유동 해석
김수미(S. M. Kim),양수석(S. S. Yang),이대성(D. S. Lee) 한국전산유체공학회 1997 한국전산유체공학회지 Vol.2 No.2
A reliable computational solver has been developed for the analysis of three-dimensional inviscid compressible flows around a nacelle of a high bypass ratio turbofan engine. The numerical algorithm is based on the modified Godunov scheme to allow the second order accuracy for space variables, while keeping the monotone features. Two step time integration is used not only to remove time step limitation but also to provide the second order accuracy in a time variable. The multi-block approach is employed to calculate the complex flow field, using an algebraic, conformal, and elliptic method. The exact solution of Riemann problem is used to define boundary conditions. The accuracy of the developed solver is validated by comparing its results around the isolated nacelle in the cruise flight regime with the solution obtained using a commercial code "RAMPANT."
이주용(Lee, J.Y.),이재형(Lee, J.H.),이대성(Lee, D.S.),이원석(Lee, W.S.),김세준(Kim, S.J.),허대기(Huh, D.G.),김현태(Kim, H.T.) 한국신재생에너지학회 2008 한국신재생에너지학회 학술대회논문집 Vol.2008 No.10
Electrical resistivity in hydrate-bearing sediments is sensitive to porosity, gas hydrate saturation, gas content, pore fluid composition, and temperature, so electrical measurements such as well logs and electromagnetic surveys have been used to explore gas hydrate-bearing formation. The high pressure tomography cell is designed considering the effect of electrode configuration and electrical shielding on tomography measurements and the safety. The evolution of electrical conductivity during CO₂ hydrate formation and dissociation reflects the combined effects of concurrent changes that include ionization of dissolved CO₂, temperature-dependent ionic mobility, changes in the degree of saturation, ion exclusion, surface conduction, and porosity changes. Measurements during hydrate formation and dissociation require careful analysis to properly interpret signatures, in particular when out-of plane conductivity anomalies prevail.
비장착 엔진/나셀 형상에 대한 3차원 Euler 유동 해석
김수미(S. M. Kim),양수석(S. S. Yang),이대성(D. S. Lee) 한국전산유체공학회 1997 한국전산유체공학회지 Vol.2 No.2
A reliable computational solver has been developed for the analysis of three-dimensional inviscid compressible flows around a nacelle of a high bypass ratio turbofan engine. The numerical algorithm is based on the modified Godunov scheme to allow the second order accuracy for space variables, while keeping the monotone features. Two step time integration is used not only to remove time step limitation but also to provide the second order accuracy in a time variable. The multi-block approach is employed to calculate the complex flow field, using an algebraic, conformal, and elliptic method. The exact solution of Riemann problem is used to define boundary conditions. The accuracy of the developed solver is validated by comparing its results around the isolated nacelle in the cruise flight regime with the solution obtained using a commercial code RAMPANT.