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비정렬 중첩격자기법을 이용한 수중추진기 주의의 점성유동 해석
안상준(S.J. An),권오준(O.J. Kwon),정영래(Y.R. Jung) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
In this paper, viscous flow calculation of pump-jet that is used as underwater propulsor was made by using RANS equation. For the validation, calculation for DTRC4119 marine propeller was made and reasonable agreements were obtained between the present results and the experiment. An unstructured overset mesh technique is used for analysis of relative motion between rotor and stator in pump-jet propulsor. Results for pump-jet propulsor were compared with computational results of another researcher.
비정렬 격자계에서 균질혼합 모델을 이용한 2차원 수중익형 주위의 캐비테이션 유동 해석
안상준(S. J. An),권오준(O. J. Kwon) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
In this paper, numerical simulation of cavitation flow for modified NACA66 hydrofoil was made by using the multi-phase RANS equation based on pseudo-compressibility. The Homogeneous mixture model comprised of the mixture continuity, mixture momentum and liquid volume fraction equations was utilized. A vertex-centered finite-volume method was used in conjunction 2nd-order Roe’s FDS to discretize the inviscid fluxes. The viscous fluxes were computed based on central differencing. The Spalart-Allmaras one equation model was employed for the closure of turbulence. Reasonable agreements were obtained between the calculation results and the experiment for pressure coefficients on the hydrofoil surface.
이규란(G.R. Lee),안상준(S.J. An),권오준(O.J. Kwon) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.5
The study of stage separation and abort simulation has always been important in the development of next-generation launch vehicles. In the present study, numerical simulation of stage separation of two-stage reusable launch vehicles was made by using a two-dimensional viscous flow solver on unstructured meshes. Aerodynamic data were obtained for a matrix of longitudinal and vertical positions in the supersonic (Mach number 3) and hypersonic (Mach number 6) speeds. For these simulation, the Langley Glide-Back Booster (LGBB) configuration in a beLLy-to-belly bimese arrangement was used. The present study was conducted to investigate the interference aerodynamic characteristics and to study the proximity flow environment. The results showed that complex bow shock interactions have an impact on the proximity aerodynamic characteristics and the stability of the vehicle during the stage separation.