• 대한토목학회논문집
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• 제29권4B호
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• pp.339-346
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• 2009

본 연구에서는 조류와 충격파가 혼재한 해역의 흐름 특성을 3차원 수치모형(Princeton Ocean Model, POM)을 사용하여 파악하였다. 1994년에 완공된 시화방조제의 끝막이 공사 동안 개방구간과 그 주변 해역의 흐름을 모의하기 위하여 POM 모형을 선정하였다. 모의결과는 큰 내 외수위차와 적은 통수단면적으로 인해 발생한 충격파가 창조시와 낙조시에 각각 방조제 내측과 외해로 전파되는 것으로 나타났다. 또한, 충격파 주변에서 흐름분리가 발생하며, 충격파가 개방구간을 통과한 후 더 넓은 지역으로 퍼짐에 따라 충격파의 조류에 대한 영향은 약화되는 것으로 나타났다. 흐름의 종방향 유속분포는 충격파의 영향을 받는 것으로 밝혀졌다. 또한, 낙조시 개방구간 전방에서 수위강하가 발생했으며, 내외수위차가 가장 큰 모의조건에서는 도수현상이 발생하였다. 따라서 충격파가 지배적인 해역의 흐름 특성을 파악하기 위해서는 3차원적 수리해석이 필요하며, 해석결과는 대상해역에서 수행되는 해상공사 및 시설물 관리에 필요한 정보를 제공할 것으로 기대된다.

• 한국분무공학회지
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• 제1권3호
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• pp.37-50
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• 1996

Computational fluid dynamics was used to optimize an A/C duct. Three dimensional flow analysis in an automotive A/C duct was performed computationally using various turbulence models and compared numerical predictions such as outlet flow split, surface pressure distribution along the duct to experimental data. Additionally, we studied the effect of location variation of 2nd branch on exit flow ratio and could find optimal location of 2nd branch. The design of an A/C duct was modeled and calculated to enhance the airflow distribution in each outlet using the STAR-CD computational fluid dynamics software. In results, modified $k-\varepsilon$ turbulence model allows a successful prediction of static pressure distribution particulary at around strong curvature but little improvement flow split. In the future, adoption of CFD to design an A/C duct with modified $k-\varepsilon$ model will bring benefits of producing more accurate prediction, and also give designers more detail information much more than now.

• 한국유체기계학회 논문집
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• 제19권5호
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• pp.42-49
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• 2016

Aerodynamic analysis of a low-voltage electric motor has been performed with various inlet vent shapes. Effects of inlet vent shape on aerodynamic performance of a motor cooling fan have been investigated numerically using three-dimensional Reynolds-averaged Navier-Stokes equations. The k-${\varepsilon}$ turbulence model was used for the analysis of turbulence. The finite volume method and unstructured tetrahedral grids were used in the numerical analysis. Optimal grid system in the computational domain was selected through a grid-dependency test. From the results of the flow analysis, considerable energy loss by flow separation was observed in the flow passage. It was found that mass flow rate through the cooling fan in the low-voltage motor can be increased by modifying the inlet vent shape. And, some inlet vent shapes were suggested to improve the aerodynamic performance of the motor cooling fan.

• Journal of Mechanical Science and Technology
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• 제20권3호
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• pp.418-425
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• 2006

The present investigation deals with the study of the internal flow phenomena of the counterflow type vortex tube using experimental testing and numerical simulation. Visualization was carried out using the surface tracing method, injecting dye on the vortex tube wall using a needle. Vortex tube is made of acrylic to visualize the surface particle tracing and the input air pressure was varied from 0.1MPa to 0.3MPa. The experimentally visualized results on the tube show that there is an apparent sudden changing of the trajectory on the vortex tube wall which was observed in every experimental test case. This may indicate the stagnation position of the vortex flow. The visualized stagnation position moves towards the vortex generator with increase in cold flow ratio and input pressure. Three-dimensional computational study is also conducted to obtain more detailed flow information in the vortex tube. Calculated total pressure, static pressure and total temperature distributions in the vortex tube were in good agreement with the experimental data. The computational particle trace on the vortex tube wall is very similar to that observed in experiments.

• 대한조선학회논문집
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• 제54권1호
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• pp.18-25
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• 2017

This study deals with numerically comparing performance according to rudder shape called 'Twisted rudder and Wavy twisted rudder'. In comparison with conventional rudder, rudder with wavy shape has showed a better performance at high angles of attack($30^{\circ}{\sim}40^{\circ}$) due to delaying stall. But most of study concerned with wavy shape had been performed in uniform flow condition. In order to identify the characteristics behind a rotating propeller, the present study numerically carries out an analysis of resistance and self-propulsion for KCS with twisted rudder and wavy twisted rudder. The turbulence closure model, Realizable $k-{\epsilon}$, is employed to simulate three-dimensional unsteady incompressible viscous turbulent and separation flow around the rudder. The simulation of self-propulsion analysis is performed in two step, because of finding optimization case of wavy shape. The first step presents there are little difference between twisted rudder and case of H_0.65 wavy twisted rudder in delivered power. So two kind of rudders are employed from first step to compare lift-to-drag ratio and torque at high angles of attack. Consequently, the wavy twisted rudder is presented as a possible way of delaying stall, allowing a rudder to have a better performance containing superior lift-to-drag ratio and torque than twisted rudder at high angles of attack. Also, as we indicate the flow visualization, check the quantity of separation flow around the rudder.

• 멤브레인
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• 제29권2호
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• pp.105-110
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• 2019

다공성 분리막은 입자성 물질을 제거하는데 산업적으로 다양하게 응용되고 있다. 기존 다공성 분리막 제작 방법과 다르게, 용액퍼짐 상분리법은 매우 간단하게 기공을 형성할 수 있다. 먼저 지지층으로 메쉬 위에 물을 적신 후, 물과 혼합되지 않은 용매에 폴리설폰 용액을 흘려준다. 이때 물과 혼합되지 않은 용매는 쉽게 기화되어 폴리설폰은 얇은 막으로 만들어지게 된다. 기공을 형성하기 위해 폴리설폰 용액에 물과 혼합할 수 있는 물질을 넣게 되면, 넣어주는 농도 비율에 따라 기공크기를 조절할 수 있게 된다. 막의 두께는 쉽게 용액의 농도로 조절이 된다. 다공성 분리막은 메쉬의 형성을 그대로 유지하고 있어 3차원 구조체를 형성하는데 매우 유용하다. 본 연구에서 제시된 용액 퍼짐 상분리법은 매우 낮은 생산단가와 쉬운 공정조절에 의해 기존 분리막에 비해 높은 가격경쟁력을 가질 수 있는 특징을 보이고 있다.

• 항공우주기술
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• 제11권2호
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• pp.65-72
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• 2012

프로펠러와 고양력장치를 장착한 터보프롭 항공기에 대한 실속 특성 분석을 위해 수치 해석을 수행하였다. 항공기의 실속 특성은 프로펠러와 고양력 장치의 장착 조합에 따른 형상별 전산해석 결과를 통해 정성적으로 분석하였다. 실속 특성 해석은 Spalart-Allmaras 난류 모델을 기반으로 한 3차원 Navier-Stokes 방정식 해법을 이용하였으며 프로펠러의 회전은 슬라이딩 격자기법을 이용하여 모사하였다. 분석 결과 순항 형상의 경우 동체/날개 페어링에서 주요 유동박리가 발생하며 프로펠러 후류로 인해 점차 감소함을 알 수 있었다. 고양력장치를 장착한 경우 나셀 바깥쪽에서 주요 유동박리 현상이 발생하였고 프로펠러가 회전하는 경우에도 상대속도 감소와 유효 받음각 증가로 나셀 바깥쪽 날개 부분은 조기에 실속에 잠김을 알 수 있었다. 프로펠러는 날개의 inboard에서 하강하는 회전 방향이 프로펠러 후류로 인한 실속 지연 측면에서 유리함을 알 수 있었다.

• 대한기계학회논문집B
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• 제26권4호
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• pp.578-586
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• 2002

Flow structures around a rectangular prism have been investigated by using a PIV(Particle Image Velocimetry) technique. A thick turbulent boundary layer was generated by using spires arid roughness elements. The boundary layer thickness, displacement thickness and momentum thickness were 650mm, 117.4mm and 78mm, respectively. The ratio between the model height(40mm) and the boundary layer thickness H/$\delta$, was 0.06. The Reynolds number based on the free stream velocity and the height of the model was 7.9$\times$10$^3$. The PIV measurements were performed at three different wall normal planes. Three recirculation regions at forward facing step, top of the roof and backward facing step are clearly seen and show three dimensional features. Dramatic changes of flow patterns are observed in the wake regions in the different spanwise wall normal planes. Instead of reattachment and recirculation zone, rising streamlines are depicted at the normal planes near the side wall due to the interaction with a rising horse shoe vortex. The peak of turbulent kinetic energy occurs at the separation bubble on top of the roof and the magnitude is 2.5 times higher compared with that of the wake region.

• 한국항공우주학회지
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• 제44권2호
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• pp.99-107
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• 2016

본 연구에서는 Infra-Red Thermography(IRT) 기법을 활용한 초음속 풍동시험 시 의도치 않게 발생하는 기술적 문제에 대한 연구를 수행하였으며 이를 방지할 수 있는 방법에 대해 분석하였다. 풍동시험은 마하 3 또는 4의 두 가지 유동조건에서 초고속 비행체 형상을 모사할 수 있는 이중 압축램프 모델로 수행하였다. 획득된 IR 결과를 shadowgraph 가시화 이미지, 수치해석 결과와 비교하였으며 본 IRT 기법을 활용하여 초음속 이중 압축램프에서 발생하는 유동천이, 박리 그리고 3차원 현상에 관한 정성적인 정보를 획득할 수 있음을 확인하였다.

• 한국자동차공학회논문집
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• 제2권1호
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• pp.9-25
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• 1994

In the present study, the Reynolds-averaged Navier-Stokes equations, together with the equations of the $k-{\varepsilon}$ model of turbulence, were solved numerically in a general body-fitted coordinate system for three-dimensional turbulent flows around the six basic shapes of the magnetically levitated train(MAGLEV). The numerical computations were conducted on the MAGLEV model configurations to provide information on shapes of this type very near the elevated track at a constant Reynolds number of $1.48{\times}10^{6}$ based on the body length. The coordinate system was generated by numerically solving a set of Poisson equations. The convective transport equations were discretized using the finite-analytic scheme which employed analytic solutions of the locally-linearized equations. A time marching algorithm was employed to enable future extensions to be made to handle unsteady and fully-elliptic problems. The pressure-velocity coupling was treated with the SIMPLER-algorithm. Of particular interests were wall effect by the elevated track on the aerodynamic forces and flow characteristics of the six models calculated. The results indicated that the half-circle configuration with extended sides and with smooth curvature of sides was desirable because of the low aerodynamic forces and pitching moment. And it was found that the separation bubble was occured at wake region in near the elevated track.