• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 The Fifth Asian Computational Fluid Dynamics Conference
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• pp.263-265
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• 2003

The aerodynamic performance of a shrouded tail rotor in hover has been studied by using a compressible inviscid flow solver on unstructured meshes. The numerical method is based on a cell­centered finite-volume discretization and an implicit Gauss-Seidel time integration. The results show that the performance of an isolated rotor without shroud compares well with experiment. In the case of a shrouded rotor, correction of the collective pitch angle is made such that the overall performance matches with experiment to account for the uncertainties of the experimental model configuration. Details of the flow field compare well with the experiment confirming the validity of the present method.

• 한국공작기계학회:학술대회논문집
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• 한국공작기계학회 1995년도 추계학술대회 논문집
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• pp.60-63
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• 1995

The behavior of the work materials in the chip-tool interface in extremely high strain rates and temperatures is more that of viscous liquids than that of normal solid metals. In these circumstances the principles of fluid mechanics can be invoked to describe the metal flow in the neighborhood of the cutting edge. In the present paper an Eulerian finite element model is presented that simulates metal flow in the vicinity of the cutting edge when machining a low carbon steel with carbide cutting tool. The work material is assumed to obey visco-plastic (Bingham solid) constitutive law and Von Mises criterion. Heat generation is included in the model, assuming adiabatic conditions within each element. the mechanical and thermal properties of the work material are accepted to vary with the temperature. The model is based on the virtual work-stream function formulation, emphasis is given on analyzing the formation of the stagnant metal zone ahead of the cutting edge. The model predicts flow field characteristics such as material velocity effective stress and strain-rate distributions as well as built-up layer configuration

• International Journal of Aeronautical and Space Sciences
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• 제7권1호
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• pp.27-42
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• 2006

A method to design the contour and conception of a plug nozzle of arbitrary shape, but specified exit flow conditions is presented. Severals shapes can be obtained for exit Mach number by changing the specific heats ratio. The characteristics of the nozzle in terms of length, weight and pressure force exerted on the wall are compared to the Minimum Length Nozzle and found to be better. Our field of study is limited to the supersonic mode to not to have the dissociation of the molecules. The design method is based on the use of the Prandtl Meyer function of a perfect gas. The flow is not axial at the throat, which may be advantageous for many propulsion applications. The performance benefits of the plug nozzle compared to the Minimum Length Nozzle are also presented.

• Advances in aircraft and spacecraft science
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• 제3권3호
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• pp.259-269
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• 2016

In this work results from an underwater experiment on flow-induced noise in the interior of a towed body generated from a surrounding turbulent boundary layer are presented. The measurements were performed with a towed body under open sea conditions at towing depths below 100 m and towing speeds ranging from 2.4 m/s to 6.2 m/s (4 kn to 12 kn). Focus is given in the experiments to the relation between (outer) wall pressure fluctuations and the (inner) hydroacoustic near-field on the reverse side of a flat plate. The plate configuration consists of a sandwich structure with an (thick) outer polyurethane layer supported by an inner thin layer from fibre-reinforced plastics. Parameters of the turbulent boundary layer are estimated in order to analyse scaling relations of wall-pressure fluctuations, interior hydroacoustic noise, and the reduction of pressure fluctuations through the plate.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집E
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• pp.690-695
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• 2001

The three-dimensional spatial structures of impeller flow created by a six bladed Rushton turbine have identified based on the volumetric velocity information from multi-plane stereoscopic PIV measurements. A total of 10 planes with 2 mm space with a 50 mm by 64 mm size of the field of view were targeted. To reduce the depth of focus, we adopted an angle offset configuration which satisfied the Scheimpflug condition. The distortion compensation procedure was utilized during the in situ calibration. Phase-locked instantaneous data were ensemble averaged and interpolated in order to obtain mean 3-D, volumetric velocity fields on a 60 degree sector of a cylindrical ring volume enclosing the turbine blade. Using the equi-vorticity surface rendering, the spatial structure of the trailing vortices was clearly demonstrated. Detail flow characteristics of the radial jet reported in previous studies of mixer flows were easily identified.

• 대한기계학회논문집B
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• 제27권6호
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• pp.773-780
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• 2003

The three-dimensional spatial structures of impeller flow created by a six bladed Rushton turbine have identified based on the volumetric velocity information from multi-plane stereoscopic PIV measurements. A total of 10 planes with 2 mm space and a 50 mm by 64 mm size of the field of view were targeted. To reduce the depth of focus, we adopted an angle offset configuration which satisfied the Scheimpflug condition. The distortion compensation procedure was utilized during the in situ calibration. Phase-locked instantaneous data were ensemble averaged and interpolated in order to obtain mean 3-D. volumetric velocity fields on a 60 degree sector of a cylindrical ring volume enclosing the turbine blade. Using the equi-vorticity surface rendering, the spatial structure of the trailing vortices was clearly demonstrated. Detail flow characteristics of the radial jet reported in previous studies of mixer flows were easily identified.

• 한국화재소방학회논문지
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• 제27권6호
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• pp.64-69
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• 2013

본 연구에서는 엔진 나셀 화재를 모사하고 이전의 실험결과를 보충하기위해 이차원 둔각물체 주위의 반응유동장에 대하여 수치해석을 수행하였다. Direct numerical simulation (DNS) 기반의 fire dynamic simulator (FDS)를 이용하여 반응유동장의 특성을 조사하였고, 실험결과와의 비교를 통해 화학반응식을 결정하였다. 산화제는 공기를 사용하였고, 연료는 메탄을 사용하였다. 동축류와 대향류 분사 모두의 경우에 화염의 안정성이나 모양은 둔각물체 주위의 와 강도와 크기에 크게 영향을 받았다. 동축류 분사의 경우 계산에 통한 화염소화한계를 결정하였는데 연료유속이 커질수록 공기의 유속 또한 커지는 경향이 있었고, 그 속도들 또한 기존의 실험결과와 잘 일치함을 볼 수 있었다. 유동장 특성에 대한 화학반응의 효과를 고찰하기 위해 반응이 없는 경우를 계산하여 비교하였다. 모든 경우에 비반응 유동장에 비해 반응 유동장의 후류와는 크기도 감소하고 세기도 감소함을 볼 수 있었는데 이는 반응에 의한 후류의 온도증가가 유체의 밀도 및 모멘텀을 감소시켰기 때문으로 판단된다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.445-450
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• 2011

금속분말을 연소시키기 위한 스월 연소기 설계의 기초단계로써 단일 접선 공급유로를 갖는 스월 혼합챔버를 제작하고 Paticle Image Velocimetry(PIV)를 사용하여 스월 혼합챔버의 내부 유동장 측정실험을 수행하였다. 상온의 공기를 작동유체로 사용하였으며 접선 공급유량이 증가하는 경우의 스월 혼합 챔버 내 축방향 및 접선방향 성분 속도를 획득하였다. 측정된 유동장을 바탕으로 스월유동과 역압력 구배로 인해 발생하는 외부 유입유동간의 혼합특성을 평가 하였다.

• 대한전기학회논문지:시스템및제어부문D
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• 제50권10호
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• pp.494-501
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• 2001

In this study, the effects of vascular parameter changes and electrodes on VOP measurement based on IPG were simulated mathematically. For the evaluation of the effects of hemodynamic changes on VOP, a mathematical model, which consists of cardiovascular system model and venous occlusion model, was developed and the model solution representing the blood flow and pressure in measuring point was found by 2nd order Runge-Kutta method. And, with sensitivity coefficients obtained from finite element solution of electric field in measuring point, the effects of electrode system on measurement were evaluated. As increasing the resistance, the venous capacitance was not changed but the venous outflows were decreased and the decreased compliance reduced the venous capacitance. And, for several configurations of round electrodes and band electrodes, the sensitivity coefficients were computed using the electric field distribution along deep vein. In conclusion, the proposed mathematical cardiovascular model could be applied to the simulation study on the effects of hemodynamic parameters on DVT diagnosis with IPG. And, also the sensitivity coefficients could provide effective electrode configuration for exact measurement of VOP.

• 한국추진공학회지
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• 제3권2호
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• pp.82-91
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• 1999

초폭굉 램 가속기의 탄체 형상은 탄체 주위에 형성되는 충격파의 구조 및 데토네이션파의 생성, 그리고 탄체의 가속 특성에 커다란 영향을 주게 된다. 본 연구에서는 초폭굉 모드의 기본 탄체 형상인 원추-원퉁-원추의 전.후면 반 꼭지각의 변화와 이중 원추, 그리고 Power-Law 형상 등의 탄체 전면 형상의 변화가 탄체 주위의 유동장, 데토네이션파의 형성 과정, 그리고 탄체 가속 특성에 미치는 영향을 수치적으로 해석하였으며, 이중 원추면의 높이와 각도를 변화시킴으로써 전.후면 반 꼭지각이 $10^{\cire}$인 ISL의 기본 형상에 비하여 약 31.0%의 향상된 가속 성능을 갖는 램 가속기 탄체 형상을 도출하였다. 이러한 탄체 가속 특성 연구 결과는 향후 램 가속기에 대한 설계 최적화 연구에 유용한 자료로 이용 될 것이다.