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신재렬(J.R. Shin),김한영(H.Y. Kim),김대영(D.Y. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
This study is performance estimation of wind augmentation device for BiWP(Building-integrated Wind Power) which recently attracts attention as a local power. various structures are installed on a rooftop of residential complex buildings and other high rise apartment buildings. Changing a profile of these, we designed a configuration that is able to capture much air and increase exit velocity. To estimate wind augmented effect of this device, we compared numerical analysis results with wind tunnel test results. Results show that exit velocity is increased from 24% to 60% by wind augmented device on a rooftop of building and uniform velocity profile is got for comparison without concerning wind augmentation.
신재렬(J.-R. Shin),김명호(M.-H. Kim),최정열(J.-Y. Choi) 한국전산유체공학회 2001 한국전산유체공학회 학술대회논문집 Vol.2001 No.-
Aparallel computing environment was constructed based on Windows 2000 operating system. This cluster was configured using Fast-Ethernet system to hold up together the clients within a network domain. For the parallel computation, MPI implements for Windows such as MPICH.NT.1.2.2 and MP-MPICHNT.1.2 were used with Compaq Visual Fortran compiler which produce a well optimized executives for x86 systems. The evaluation of this cluster performance was carried out using a preconditioned Navier-Stokes code for the 2D analysis of a compressible and viscous flow around a compressor blade. The parallel performance was examined in comparison with those of Linux clusters studied previously by changing a number of processors, problem size and MPI libraries. The result from the test problems presents that parallel performance of the low cost Fast~Ethernet Windows cluster is superior to that of a Linux cluster of similar configuration and is comparable to that of a Myrinet cluster.
초음속 유동장에서 기저 유동의 Detached Eddy Simulation
신재렬(J.R. Shin),원수희(S.H. Won),최정열(J.Y. Choi) 한국전산유체공학회 2008 한국전산유체공학회 학술대회논문집 Vol.2008 No.-
Detached Eddy Simulation (DES) is applied to an axisymmetric base flow at supersonic mainstream. DES is a hybrid approach to modeling turbulence that combines the best features of the Reynolds-averaged Navier-Stokes (RANS) and large-eddy simulation (LES) approaches. In the Reynolds-averaged mode, the model is currently based on either the Spalart-Allmaras (S-A) turbulence model. In the large eddy simulation mode, it is based on the Smagorinski subgrid scale model. Accurate predictions of the base flowfield and base pressure are successfully achieved by using the DES methodology with less computational cost than that of pure LES and monotone integrated large-eddy simulation (MILES) approaches. The DES accurately resolves the physics of unsteady turbulent motions, such as shear layer rollup, large-eddy motions in the downstream region, small-eddy motions inside the recirculating region. Comparison of the results shows that it is necessary to resolve approaching boundary layers and free shear-layer velocity profiles from the base edge correctly for the accurate prediction of base flows. The consideration of an empirical constant CDES for a compressible flow analysis may suggest that the optimal value of empirical constant CDES may be larger in the flows with strong compressibility than in incompressible flows.
평형화학반응과 복사열전달을 고려한 로켓 플룸 유동 해석
신재렬(J.-R. Shin),최정열(J.-Y. Choi),최환석(H.-S. Choi) 한국전산유체공학회 2004 한국전산유체공학회 학술대회논문집 Vol.2004 No.-
The Numerical study has been carried out to investigate the effects of chemical reaction and thermal radiation on the rocket plume flow-field at various altitudes. The theoretical formulation is based on the Navier-Stokes equations for compressible flows along with the infinitely fast chemistry and thermal radiation. The governing equations were solved by a finite volume fully-implicit TVD(Total Variation Diminishing) code which uses Roe's approximate Riemann solver and MUSCL(Monotone Upstream-centered Schemes for Conservation Laws) scheme. LU-SGS (Lower Upper Symmetric Gauss Seidel) method is used for the implicit solution strategy. An equilibrium chemistry module for hydrocarbon mixture with detailed thenno-chemical properties and a thermal radiation module for optically thin media were incorporated with the fluid dynamics code.<br/> n this study, kerosene-fueled rocket was assumed operating at O/F ratio of 2.34 with a nozzle expansion ratio of 6.14. Flight conditions considered were Mach number zero at ground level, Mach number 1.16 at altitude 5.06km and Mach number 2.9 at altitude 17.34km. Numerical results gave the understandings on the detailed plume structures at different altitude conditions. The diffusive effect of the thermal radiation on temperature field and the effect of chemical recombination during the expansion process could be also understood. By comparing the results from frozen flow and infinitely fast chemistry assumptions, the excess temperature of the exhaust gas resulting from the chemical recombination seems to be significant and cannot be neglected in the view point of performance, thermal protection and flow physics.
INSTABILITY OF OBLIQUE SHOCK WAVES WITH HEAT ADDITION
J.Y. Choi(최정열),J-R. Shin(신재렬),D.R. Cho(조덕래) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
A comprehensive numerical study was carried out to identify the on-set condition of the cell structures of oblique detonation waves (ODWs). Mach 7 incoming flow was considered with all other flow variables were fixed except the flow turning angles varying from 35 to 38. For a given flow conditions theoretical maximum turning angle is 38.2° where the oblique detonation wave may be stabilized. The effects of grid resolution were tested using grids from 255×100 to 4,005×1,600. The numerical smoked foil records exhibits the detonation cell structures with dual triple points running opposite directions for the 36 to 38 turning angles. As the turning angle get closer to the maximum angle the cell structures gets finer and the oscillatory behavior of the primary triple point was observed. The thermal occlusion behind the oblique detonation wave was observed for the 38° turning angle.
TBCC를 위한 CVC 엔진의 데토네이션 현상 기초 연구
최정열(J.-Y. Choi),Bernard Parent,조덕래(D.-R. Cho),강기하(K. Kang),신재렬(J.-R. Shin),이수한(S.-H. Lee),이태형(T.-H. Yi) 한국추진공학회 2008 한국추진공학회 학술대회논문집 Vol.2008 No.11
DARPA가 계획 중인 대형 극초음속 추진 기관 개발 프로그램 VULCAN 프로그램은 듀얼모드 램제트/스크램제트 엔진과 연계되어 TBCC엔진을 이룰 수 있도록, 기존의 터보제트(또는 터보팬) 엔진과 CVC과 엔진을 결합하여 마하수 4이상에서 작동 가능한 엔진을 개발하는 것을 목표로 하고 있다. CVC 엔진은 데토네이션 연소 현상을 기본으로 하여 고마하수에서 고효율을 얻을 수 있는 PDE 이나 CDE와 같은 신개념의 엔진이다. 본 논문에서는 부산대학교 항공우주공학과 연소 추진 연구실에서 지난 수년간 국제공동 연구의 형태로 수행한 데토네이션 현상의 추진기관 응용에 연구에 대하여 소개한다. DARPA"s hypersonic propulsion program VULCAN is aimed for development of Mach 4+ capable engine by combining current production turbofan engine such as F119 with CVC (Constant Volume Combustion) engine. Final goal is a TBCC(Turbo-based Combined Cycle) engine by combining with dual mode ramjet/scramjet engine. CVC is a common designation of new concept of high efficiency engines, such as Pulse Detonation Engine (PDE) or Continuous Detonation Engine (CDE), which use the detonation as a combustion mechanism. Present paper introduces the internationally collaborative research activities carried out in Aerospace Combustion and Propulsion Laboratory of the department of Aerospace Engineering of the Pusan national University.
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.