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최성욱(S. W. Choi),장근식(K. S. Chang) 한국전산유체공학회 2000 한국전산유체공학회 학술대회논문집 Vol.2000 No.5
Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated using a two-dimensional turbulent compressible Navier-Stokes flow model. The spoiler moving relative to a stationary airfoil is treated by an overset grid bounded by a 'dynamic domain-dividing line' the concept of which is developed first in this paper. The fluid-dynamic mechanism of the adverse lift due to the rapidly deploying spoiler is analyzed. Also the effect of spoiler deploying rate on the initial behavior of the aerodynamic response is expounded, which is of interest in view of active control technology and controller design for the spoiler. The results of present computation about the stationary as well as moving spoilers are relatively in good agreement with the existing experimental data.
탄성체-삼투압 약물주입펌프 성능 최적화를 위한 시뮬레이션
김동선(D. S Kim),강성민(S. M. Kang),김의찬(E. C. Kim),최성욱(S. W. Choi) 대한기계학회 2015 대한기계학회 춘추학술대회 Vol.2015 No.11
Drug infusion pump is classified as electronic and mechanical. Electronic drug infusion pump precision control is possible by using a motor, but it is not easy to carry and it is expensive. The mechanical drug infusion pump can be portable and operations to use the easy. However, mechanical infusion pump flow rate is not constant. Therefore, there was a lot of attempts to solve the problems of the Mechanical infusion pump, there is a combination of elastomeric and osmotic pressure of the drug infusion. but this of elastomeric and osmotic infusion pumps is important to elasticity and concentration of difference because of injecting by interaction between elastic and osmotic pressure. Therefore, in this paper indicates interaction between the elasticity and concentration differences. Performance of the infusion pump is optimized by simulation programs.
최성욱(S.W. Choi),김인선(I.S. Kim) 한국전산유체공학회 2001 한국전산유체공학회 학술대회논문집 Vol.2001 No.-
Flow computations have been conducted to study the impingement flow field over the KSR-Ⅲ flume deflector. To validate Euler solver for the jet impingement flowfield, the jet flow over a double wedge deflector have been calculated and showed reasonable agreement with experimental data. The transient flow behavior of flume over deflector have been investigated and the flume from the rocket nozzle proved to he getting out of the deflector safely and the thermal effect on the base region of rocket was not considerable.
2-방정식 난류모델을 이용한 스포일러 천이적 공력특성의 파라메트릭 연구
최성욱(S. W. Choi),장근식(K. S. Chang),옥호남(H. N. Ok) 한국전산유체공학회 2000 한국전산유체공학회 학술대회논문집 Vol.2000 No.10
The transient response of an airfoil to a rapidly deploying spoiler is numerically investigated using the turbulent compressible Navier-Stokes equations in two dimensions. Algebraic Baldwin-Lomax model, Wilcox k- ω model, and SST k- ω turbulence model are used to calculate the unsteady separated flow due to the rapid spoiler deployment. The spoiler motion relative to a stationary airfoil is treated by an overset grid bounded by a Dynamic Domain-Dividing Line which has been devised by the authors. The adverse effects of the spoiler influenced by the spoiler location and the hinge gap are expounded. The numerical results are in reasonably good agreement with the existing experimental data.
보존적 중첩격자기법을 이용한 동적 플랩의 천이적 공력거동에 관한 수치적 연구
최성욱(S. W. Choi),장근식(K. S. Chang) 한국전산유체공학회 1999 한국전산유체공학회 학술대회논문집 Vol.1999 No.-
Transient aerodynamic response of an airfoil to a moving plane. flap is numerically investigated using two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a' dynamic domain, dividing line' the concept of which is developed in this study. A conservative Chimera grid method with a dynamic domain-dividing line technique is applied and validated by solving the flowfield around circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver is also examined by computations of a oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.
최성욱(S.W. Choi),김재무(J.M. Kim) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
Unsteady flow simulation for the tiltrotor Smart UAV configuration was performed to investigate the powered rotor wake effect on aerodynamic characteristics. Calculations were performed to simulate various flow conditions based on different flight modes including hover, conversion and cruise. Three-dimensional compressible Navier-Stokes equation code were used for flow calculation and Chimera grid technique overlapping individually generated grids was employed A dynamic grid method was adopted in simulation of the rotating blades. Flow calculations were also conducted for the un-powered case. Aerodynamic interaction between the rotor and airframe was investigated comparing three data sets from the un-powered, powered, and isolated rotor cases.