• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.293-298
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• 2005

We calculate the coordinates of an axisymmetric nozzle with a central body. This nozzle ensures a transonic flow with a plane sound surface, which is orthogonal to the symmetry axis and has a wall kink at the sonic point, The Chaplygin transformation in the subsonic part of the flow leads the Dirichlet problem for a system of nonlinear equations. The definition domain of the solution in the velocity-hodograph plane is taken as a rectangle. This enables one to obtain the nozzle with a monotonic distribution of velocity along its subsonic part. In the nonlinear differential equation, the linear Chaplygin operator for plane flows is separated, which allows the iterative calculation of the solution. The supersonic part of the nozzle is calculated under the assumption that the flow at the nozzle exit is uniform and parallel to the symmetry axis; i.e., the supersonic jet outflows to the submerged space with the same pressure. The calculation is performed by the characteristic method. The exact solution of Tricomi equation for near-sonic flows with the straight sonic line is used to 'move away' the sound plane. The velocity distribution alone the supersonic part of the nozzle is also monotonic, which ensures the absence of the boundary-layer separation and, therefore, the adequacy of the ideal-gas model. calculations show that the flow in the supersonic part of the nozzle is continuous (compression shocks are absent)

• 대한기계학회논문집
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• 제17권2호
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• pp.416-425
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• 1993

To investigate the characteristics of the merged jet arising from the interaction of two opposing curved wall jets over a circular cylinder in still air, mean velocity, Reynolds stresses, triple moments and integral length scale were measured using hot-wire anenometry. The turbulent kinetic energy and shear stress budget were evaluated using the measured data. The variations of the Reynolds stresses, the triple moment and integral length scale are severe in the interaction region. The pressure diffusion terms are found to be very large when compared the other terms in the interaction region. The distributions of the Reynolds stress and the triple moment in the similar region are found to be similar to those of conventional plane jets.

• 대한토목학회논문집
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• 제7권1호
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• pp.11-22
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• 1987

흐름수역(水域)에서 연직상향으로 방류되는 평면부력(平面浮力)?의 거동이 연속방정식(連續方程式), 운동량방정식(運動量方程式) 및 추적물수송식(追跡物輸送式)의 기본방정식을 수치적(數値的)으로 풀음으로서 해석(解析)된다. 난류확산(亂流擴散)에는 Prandtl의 혼합거리이론(混合距離理論)을 도입한 난류수송모형(亂流輸送模型)이 이용된다. 수치해과정(數値解過程)은 기본방정식을 유함수(流凾數)(stream function)식(式)과 골도수송(滑度輸送)(vorticity transport)식을(式) 이용하여 변환(變換)한 후, ?방류속도(放流速度), ?방류구폭(放流口幅) 등(等)으로 표현되는 변수(變數)와 흐름을 지배(支配)하는 무차원매개변수(無次元媒介變數)를 도입하여 무차원화(無次元化)하고 successive under-relaxation을 이용하여 Gauss-Seidal 반복법(反復法)으로 해를(解) 구(求)하는 것이다. 수치실험(數値實驗)은 방류(放流)Froude수(數)가 4~32, 방류속도(放流速度)와 가로흐름속도와의 비로(比) 정의되는 속도비가 8~15 의 범위의 흐름영역(領域)에서 수행되었다. 부력(浮力)?으로 인한 주변(周邊)흐름수역(水域)의 속도변화(速度變化), 온도상승(溫度上昇)범위, 흐름상태 및 골도(滑度)가 조사되었으며, ?의 경로에 대한 속도비와 방류밀도Froude 수의 영향이 또한 조사되었다. ?중심선의 속도, 온도변화, 국부밀도(局部密度)Froude 수(數)의 변화가 계산되며 퍼짐율(spreading rate)과 확산비(擴散比)(dispersion ratio)가 방류밀도(放流密度)Froude 수, 국부밀도(局部密度)Froude 수(數) 및 속도비(速度比)의 항(項)으로 해석되었다. 또한 속도와 온도분포를 상사(相似)(similarity)로 나타낼 수 있음이 밝혀졌으며, Gaussian 분포(分布)를 이용한 적분형해석(積分型解析)(integral type analysis)이 가능한 것으로 사료된다.

• 항공우주기술
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• 제11권1호
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• pp.145-157
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• 2012

상평면상에서 추력기를 사용하는 자세제어 시스템의 리밋 사이클을 해석하는 새로운 기법이 논문에 의해서 제안되었다. 그러나 이것은 소프트 시뮬레이션상에서 Haloulakos 방식보다 제안 방식이 정확함을 보였지만, 실제 시스템으로 검증하지는 못하였다. 그래서 저자의 제안 방식을 KSLV-I 추력기 자세제어 시스템에 대한 실시간 모의시험으로 검증하고, 리밋 사이클 해석에 대하여 실시간 모의시험 결과와 이론적으로 구한 값을 비교/분석하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 The Fifth Asian Computational Fluid Dynamics Conference
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• pp.107-109
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• 2003

We propose a wall distance free one-equation turbulence model. The model is organized in an extremely simple form. Only a few model constants were introduced into the model. The model is numerically tough and easy-of-use. The model also demonstrated the ability to simulate the laminar to turbulent flow transition. The model has been applied to the channel flow, the plane jet, the backward facing step flow, the flat plate boundary layer, as well as the flow around the 2D airfoil at large angles of attack, which obtained satisfactory results.

• 한국수자원학회:학술대회논문집
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• 한국수자원학회 1987년도 제29회 수공학연구발표회논문초록집
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• pp.89-97
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• 1987

가로흐름에 방류되는 연직평면부력젤의 젤중심선경로와 온도분포를 실험자료와 기본방정식으로부터 유도된 적분식에 의하여 해석한다. 기본방정식으로부터 적분식의 유도는 상사법칙과 특성길이를 도입하여 연직상향 및 수평방향흐름영역에 대한 차원해석을 하였고, 실험은 속도비(R=Wo/Ua)와 방류밀도Froude수를 변화시키면서 각각에 따른 젤중심선경로와 온도분포를 획득하였다. 속도비 R과 방류밀도Froude수 Fo에 따라 부력젤의 흐름특성은 달라지게 되며, 초기조건(운동량및 부력)에관계없이 부력젤은 항상 운동량지배영역이 존재함을 알 수 있었고 적분식에 의한 역법칙(power law)과 실험 자료는 대체로 일치된결과를 나타내었다.

• 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.

• 대한기계학회논문집B
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• 제24권2호
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• pp.195-203
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• 2000

The local heat/mass transfer coefficients for arrays of impinging circular air jets on a plane surface are determined by means of the naphthalene sublimation method. Fluid from the spent jets is constrained to flow out of the system in one direction. Therefore, the spent fluid makes a crossflow in the confined space. The present study investigates effects of jet-orifice-plate to impingement-surface spacing and jet Reynolds number. The spanwise- and overall-averaged heat/mass transfer coefficients are obtained by numerical integrating the local heat transfer coefficients. The local maximum heat/mass transfer coefficients move further in the downstream direction due to the increase of crossflow velocity. At the mid-way between adjacent jets, the heat/mass transfer coefficients have a small peak owing to the collision of the adjacent wall jets and are affected strongly by the crossflow. The effect of the crossflow occurs strongly at the small orifice-to-impingement surface distance.

• 한국화재소방학회논문지
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• 제18권2호
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• pp.41-48
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• 2004

선박 기관실의 고정식 소화장치로 사용되는 $CO_2 $ 소화장치의 소화효과에 영향을 미칠 수 있는 인자 중 분사노즐위치를 변화시켜 이산화탄소 소화제 전달특성에 대한 전산모이실험을 3차원 비정상상태로 수행하였다. 노즐위치에 따라 유동장과 $CO_2$ 소화제 농도장을 계산하였다 소화제 분사노즐을 공간의 천장 중앙에 매치 한 경우, 천장에 형성되는 대칭 천장 제트가 대칭면에서 서로 부딪혀 저농도 하향 유동을 발생시켜 분사주위에는 규정농도 이하의 농도분포를 형성시킨다. 벽의 모서리에서는 소화제질량전달이 촉진되는 경향으로 인해 농도곡선은 모서리 부근에서 피크를 나타낸다.