• Proceedings of the Korean Nuclear Society Conference
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• 1998.05a
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• pp.699-706
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• 1998

한국원자력연구소에서는 원자력중장기연구의 일환으로 한국형 표준원전을 모의하는 종합열수력실증실험을 계획하고 있으며, 현재 실험장치에 대한 척도해석(Scaling Analysis), 예비해석(Scoping Analysis) 및 개념설계를 수행하고 있다. 본 논문에서는 영광 3/4호기를 대상으로 척도해석을 통하여 실험장치를 개념설계하고, 저온관 6인치 소형냉각재 상실사고에 대하여 예비해석을 수행한 결과를 보여준다. 개념설계된 실험장치는 높이비가 참조원자로와 동일하고, 체적비가 1/200이다. 실험장치의 개념설계는 이상유동에 대한 3단계 척도법을 적용하였으며, 개념설계의 타당성을 입증하기 위해 RELAP5/MOD3.1 코드를 사용하여 정상상태 및 저온관 6인치 소형냉각재 상실사고시 계통의 거동을 예비 계산하였다. 실험장치에 대한 예비해석결과 사고 거동이 참조원자로와 잘 일치하는 것으로 나타났다. 또한 수평관 및 주냉각재펌프의 척도기준이 사고의 진행과정에 영향을 미치는 중요한 인자로 밝혀졌다

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.2
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• pp.39-45
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• 2000

A Thruster valve operates to supply fuel into thruster chamber. Very quick on-off operation of thruster valve results in unsteady flow of fuel in the propellant supplying system. Then fuel kinetic force, elastic material of propellant line, compressibility of fuel cause the flow field to pulsate. The pressure oscillation arising from resonance would damage the weak part of the thruster valve and other propellant supplying equipment. Pressure drop and fuel flowrate through propellant suppling system were measured, and pressure oscillation were triggered at the thruster valve inlet.

• Transactions of the Korean Society of Automotive Engineers
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• v.2 no.5
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• pp.66-73
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• 1994

The configuration effects of a tumble adaptor which transforms tumble into swirl on the intake tumble characterization under steady flow condition have been investigated by LDV measurement The following parameters were involved to test their effects on tumble-swirl conversion characteristics ; the cylinder height and its bottom shape, measuring position in the swirl induction pipe, and the relative direction of the induction pipe. The short cylinder height and the flat bottom of the tumble adaptor were found effective for the generation of tumble in the cylinder, allowing higher tumble-swirl conversion efficiency.

• Journal of the Korean Society of Propulsion Engineers
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• v.1 no.1
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• pp.8-23
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• 1997

Steady and unsteady numerical simulations are conducted for the comparison with the experiments performed to investigate the ram accelerator flow field by using an expansion tube facility in Stanford University. Wavier-Stokes equations for chemically reacting flows are analyzed by fully implicit and time accurate numerical methods with Jachimowski's detailed chemistry model for hydrogen-air combustion involving 9 species and 19 reaction steps. Although the steady state numerical simulation shows a good agreement with the experimental schlieren and OH PLIF images for the case of $2H_2$＋$O_2$＋$17N_2$ fails in reproducing the combustion region behind the shock intersection point shown in the case of $2H_2$＋$O_2$＋$12N_2$ mixture. Therefore, an unsteady numerical simulation is conducted for this case and the result shows all the detailed flow stabilization process. From the result of unsteady numerical simulation, the experimental result seems to be an instantaneous state during the flow stabilization process. The combustion behind the shock intersection point is the result of a normal detonation formed by the intersection of strong oblique shocks that exist at early stage of the stabilization process. At final stage, the combustion region behind the shock intersection point disappears and the steady state result is retained. The time required for stabilization of the reacting flow in the model ram accelerator is found to be very long in comparison with the experimental test time.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.7
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• pp.647-654
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• 2010

In this study, an efficient ornithopter aerodynamic model, which is applicable to ornithopter wing design considering fluid-structure interaction or ornithopter flight dynamics and control simulation, was proposed and experimentally validated through the wind tunnel experiments. Due to the ornithopter aerodynamics governed by unsteady low Reynolds number flow, an experimental device was specially designed and developed. A part of the experimental device, 2-axis loadcell, was situated in the non-inertial frame; the dynamic calibration method was established to compensate the inertial load for pure aerodynamic load measurements. The characteristics of proposed aerodynamic model were compared with the experimental data in terms of mean and root-mean-square values of lift and drag coefficients with respect to the flow speed, flapping frequency, and fixed angle of attack.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.2
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• pp.98-107
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• 2002

An experimental and numerical study of aerodynamic charateristics of KSR-III and jet impingement on a deflector during launch has been conducted. To investigate aerodynamic characteristics of KSR-III configuration, wind tunnel tests using 6.4% scale model were performed by 4x4 feet ADD trisonic wind tunnel on the Mach number range of 0.4~3.8. Solutions of Three dimensional Euler equations were also obtained and compared with test result. For the study of KSR-III jet impingement flowfield on a deflector during launch operation, unsteady computation using CFD-FASTRAN was performed.

• Journal of the KSME
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• v.33 no.12
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• pp.1063-1068
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• 1993

왕복식엔진에서 연소과정은 실린더내 유체유동에 지배되므로 최적조건의 엔진설계를 위해서는 실린더내 유체유동을 효과적으로 이용하는 것이 필요하다. 연소과정에 중요한 영향을 미치는 압축말기 연소실내 난류강도는 흡입과정시 생성된 유동의 에너지가 압축과정을 거치면서 작은 스케일의 에디(eddy)로 깨지면서 발생된다. 연소과정시 이러한 에디들은 초기화염생성을 촉진 시키고 화염전파속도를 증진시키는 역할을 함으로써 실린더내 유체유동에 대한 이해증진을위해 실린더내 평균속도 및 난류유동을 측정하는 연구들이 많이 진행되고 있다. 엔진유동은 매사이 클의 유동이 엄밀히 주기적인 운동을 하지 않고, 각 사이클의 유동이 비정상유동을 하며, 유동의 생성 및 소멸이 매우 짧은 특성을 가진다. 따라서 산란입자가 측정체적을 통과할 때 속도데이 터가 발생하는 LDV(laser Doppler velocimetry) 측정에 있어서 레이저빔의 산란광노이즈 감소와 산란입자의 효율적인 공급으로 데이터 발생률을 높이는 것이 어려운 점이다. 이 글에서는 엔진 유동의 LDV측정시 고려해야 할 문제점들, 실험장치구성, 그리고 데이터처리 방법과 주요측정 결과에 대해 본 연구팀에서 지금까지 수행한 연구결과를 토대로 하여 기술하고자 한다.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.4
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• pp.423-429
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• 2012

Miller cycle is considered as an effective means to meet the regulation on Tier II and to reduce $CO_2$ emission. For this cycle, the amount of intake air supplied should be enough increased. Therefore, the intake system with minimized resistance for air flow is under consideration. In this study, the flow coefficients of intake valves were measured in order to obtain the basic data for the cycle simulation and intake port design. The flow coefficients were measured using the steady-flow test rig. As a test result for the poppet valve used the marine engine with medium speed, the flow coefficients are increased to about 0.62 with the valve lift. In addition it is confirmed that the flow coefficients have the characteristic value irrelevant to the S/B ratio.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 2008.04a
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• pp.199-205
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• 2008

In this study, a system to measure continuously the fuel concentration in a steady flow rig on the basis of Rayleigh scattering is presented. The system can be employed to measure both the temporal and the spatial distribution. Also, it is possible to calibrate the system for the measurement of accurate absolute concentration. Firstly, the system was tested at a calibration chamber for the determination of scattering cross section from propane, butane, acetylene, Freon-12 and Genetron 143a. After this, the system was adapted to a steady flow rig to measure the temporal and spatial fuel concentration. The rig is composed of cylinder head, intake manifold, injector, and transparent cylinder which can simulate internal combustion engine. To cope with the problem of Mie scattering interference, a software filter was developed, which is based on the rise time and the time constant of the photomultiplier-amplifier system. The results show that LRS can provide useful informations about concentration field and the software filter is very effective method to remove Mie interference.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.5
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• pp.413-422
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• 2012

The ducted fan for a small UAV propulsion can reconnoiter and observe in a town and a small area, it has better thrust efficiency and a long endurance than propeller. Thrust characteristics of hover and for ward flight condition for the ducted fan UAV is important issue to improve a endurance. The unsteady 3-dimensional flow fields of the ducted fan UAV is essential to stable flight. In this paper, to verify the design results of the ducted fan and to investigate a stable aeronautical characteristic, the thrust performance and the unsteady 3-dimensional flow fields are measured. Thrust characteristics for the hovering and the forward flight conditions are measured by the 6-components balance system in the subsonic wind tunnel. The unsteady 3-dimensional flow fields are analyzed by using a stationary $45^{\circ}$ slanted hot-wire technique. The swirl velocity is almost removed behind the stator blades. Therefore, the thrust performance of the ducted fan is improved and the flight stability is maintained.