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고압 폭발 유동장의 강도 감소를 위한 간단한 형상의 소음기에 대한 수치해석
고성호(S. H. Ko),우성대(S. D. Woo),강국정(K. J. Kang) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
A numerical analysis was made to investigate the intensity diminution of a simple silencer for high pressure blast flow fields. Reynolds-Averaged Navier-Stokes equations were solved for an axisymmetric computational domain constructed by multi block Chimera grids. A blast flow field without the silencer was also calculated to validate the present numerical method. The evolution of high pressure blast flow fields was observed by depicting calculated contours of pressure and Mach number. It was found that the tested silencer could achieve 76 percent intensity diminution.
고성호(S.H. Ko),이동수(D.S. Lee),우성대(S.D. Woo),강국정(K.J. Kang) 한국전산유체공학회 2005 한국전산유체공학회지 Vol.10 No.4
A numerical analysis was made to investigate the simple silencer for high pressure blast flow fields. Reynolds-Averaged Navier-Stokes equations were solved for an axisymmetric computational domain constructed by multi block grids. A blast flow field without the silencer was also calculated to validate the present numerical method. The effect of pressure diminution for the silencer was calculated by comparing with and without silencer at the atmosphere region. It was found that the tested silencer could achieve 89.4 percent pressure diminution.
고성호(S. H. Ko),곽영균(Y. K. Kwack),오종윤(J. Y. Oh),김윤곤(Y. K. Kim) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.11
Numerical simulation of compresible multi-phase flow involves many difficulties related to interfaces of shock, expansion waves and evaporation. It is difficult to model and compute correctly jump conditions across the interfaces. In this paper, mumerical analysis of multi-phase flows are performed using diffuse interface model for modelling liquid-gas interfaces. The reduced five equation model based on the mixture velocity and mixture pressure is used. These diffuse interfaces relaxation effects are solved in order to match the jump conditions of equal pressure and equal normal velocities. The mumerical evalustion of Riemann solver has been conducted for the classical one-dimensional shock tube and compared with exact solution for error analysis.
고성호(S.H. Ko),곽영균(Y. K. Kwack),이상현(S. H. Lee),강민구(M. K. Kang) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
A three dimensional numerical analysis has been made for the cone disk control valve and the flat disk control valve. The simulation of the incompressible flow in the each control vale are performed by using the commercial code. Six flow cases of each control valve are investigated.
겹침격자 기법을 이용한 틸트로터의 순항모드에 대한 공력성능 수치해석
고성호(S. H. Ko),안성원(S. W. Ahn),김병수(B. S. Kim) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
A numerical analysis was made for the unsteady flow fields of rotor system of a Tilt-Rotor aircraft in cruise mode. The Reynolds-averaged thin-layer Navier-Stokes equations were discretized by Roe's upwind differencing scheme and integrated in time by the LU-SGS algorithm. The computational domain of the rotor system was constructed by six multi-block Chimera grids. Simulated unsteady flow fields of rotating blades were studied in several different view points.