• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1998년도 유체기계 연구개발 발표회 논문집
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• pp.70-77
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• 1998

The rise in pressure across the impeller blade of an axial flow fan depends on the angle of attack. At a low back pressure, the air volume will be large and the angle of attack is small. The gradual increase of the back pressure approached stall zone which is not stationary but travels blade to blade passage. In consequence, a region occurs around these blades with large vibration in the flow. To avoid these stall operation, the stall detector in the axial flow fans has been designed to detect stalling condition with a manometer or differential pressure switch by electric mechanism.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2000년도 유체기계 연구개발 발표회 논문집
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• pp.325-333
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• 2000

The aerodynamics of the Wells turbine has been studied using a 3-dimensional, unstructured mesh flow solver for the Reynolds-averaged Navier-Stokes equations. The basic feature of the Wells turbine is that even though the cyclic airflow produces oscillating axial forces on the airfoil blades, the tangential force on the rotor is always in the same direction. Geometry used to define the 3-dimensional numerical grid is based upon that of an experimental test rig. The 3-dimensional Wells turbine model, consisting of approximate 220,000 cells is tested at four axial flow rates. In the calculations the angle of attack has been varied between $10^{\circ}$ and $30^{\circ}$ of blades. Representative results from each case are presented graphically and analyzed. It is concluded that this method holds much promise for future development of Wells turbines.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 추계학술대회논문집B
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• pp.615-620
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• 2000

Manoeuvrability of ships has been receiving a great deal of attention both concerning navigation safety and the prediction of ship manoeuvring characteristics, especially at the preliminary design stage. Recently, in order to improve manoeuvrability of ships, High-lift devices could be applied to design of rudder at design stage. Now, among the them, we carried out the flow visualization and investigation of flow field around a flapped rudder(trailing-edge flap). A trailing-edge flap is simply a portion of the trailing-edge section of airfoil that is hinged and which can be deflected upward or downward. Flow visualization results of flap defection shown as follow Photos including main body and flap defection.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.616-621
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA 0021 Wells turbine. The five double flaps which have 0.5% chord height difference were selected. A Navier-Stokes code, FLUENT, was used to calculate the flow field of the Wells turbine. The basic feature of the Wells turbine is that even though the cyclic airflow produces oscillating axial forces on the airfoil blades, the tangential force on the rotor is always in the same direction. Geometry used to define the 3-D numerical grid is based upon that of an experimental test rig. This paper tries to analyze the optimum double flap of Wells turbine with the numerical analysis.

• 한국유체기계학회 논문집
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• 제4권2호
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• pp.29-34
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• 2001

Experimental and numerical studies are conducted to investigate the flow field over a NACA0012 airfoil with ground effects. In experiment, the ground is simulated by a moving belt system. From the comparison between the experimental and numerical results, it is concluded that the velocity gradient over the ground plane causes the increments in pressure coefficient on lower surface of the airfoil and reduces the suction peak at the leading edge.

• 동력기계공학회지
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• 제3권1호
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• pp.29-37
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• 1999

The flow characteristics of a NACA0012 airfoil was investigated in rectangular water circulating channel. The flow patterns around an airfoil at various angles of attack between $0^{\circ}\;and\;30^{\circ}\;at\;Re=1.91{\times}104$ were visualized and measured with 2-D PIV system and laser sheet illumination. Flow behaviors such as velocity distribution, kinetic energy and flow separation etc. around an airfoil were obtained by means of 2-D PIV system. The behaviors show the difference of flow pattern clearly and separation phenomena become more active with increasing angle of attack.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2003년도 유체기계 연구개발 발표회 논문집
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• pp.520-525
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• 2003

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA0015 Wells turbine. The five double flaps which have 0.5% chord height difference were selected. A Wavier-Stokes code, CFX-TASCflow, was used to calculate the flow field of the Wells turbine. The basic feature of the Wells turbine is that even though the cyclic airflow produces oscillating axial forces on the airfoil blades, the tangential force on the rotor is always in the same direction. Geometry used to define the 3-D numerical grid is based upon that of an experimental test rig. This paper tries to analyze the optimum double flap of Wells turbine with the numerical analysis.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2003년도 유체기계 연구개발 발표회 논문집
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• pp.631-638
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• 2003

The wind turbine blade is the equipment converted wind into electric energy. The effect of the blade has influence of the output power and efficiency of wind turbine. The design of blade is considered of lift-to-drag ratio, structure, a condition of process of manufacture and stable maximum lift coefficient, etc. This study is used the simplified method for design of the aerodynamic blade and aerodynamic analysis used blade element method. This process is programed by delphi-language. The program has any input values such as tip speed ratio, blade length, hub length, a section of shape and max lift-to-drag ratio. The program displays chord length and twist angle by input value and analyzes performance of the blade.

• 수산해양기술연구
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• 제40권3호
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• pp.206-213
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• 2004

종횡비, 다각형 모양에 따른 평판과 범포의 유체역학적 특성을 규명하고자 직사각형, 사다리꼴 모양으로 모형 평판과 범포를 제작하고 회류수조에서 양 ${\cdot}$ 항력 실험을 수행하였다. 그 결과를 요약하면 다음과 같다. 1. 삼각형 평판의 경우, 종횡비가 1 이하인 모형에서는 38${\sim}$42$^{\circ}$에서 최대 $C_L$이 1.23${\sim}$1.32, 1.5 이상인 모형에서는 20${\sim}$50$^{\circ}$에서 $C_L$이 약 0.85 전후였다. 역삼각형 평판의 경우, 종횡비가 1 이하인 모형에서는 영가가 36${\sim}$38$^{\circ}$에서 최대 $C_L$이 1.46${\sim}$1.56, 1.5 이상인 모형에서는 22${\sim}$26$^{\circ}$에서 1.05${\sim}$1.21 정도였다. 같은 삼각형 평판 모형에서는 전자의 모형이 후자보다 $C_L$이 작게, 양항비도 작게 나타났다. 2. 삼각형 범포의 경우, 종횡비가 1 이하인 모형에서는 영각 46${\sim}$48$^{\circ}$에서 최대 $C_L$이 1.67${\sim}$1.77, 1.5 이상인 모형에서는 20${\sim}$50$^{\circ}$에서 $C_L$이 약 1.1 전후였다. 역삼각형 범포의 경우, 종횡비가 1 이하인 모형에서는 영각 28${\sim}$32$^{\circ}$에서 최대 $C_L$이 1.44${\sim}$1.68, 1.5 이상인 모형에서는 18${\sim}$24$^{\circ}$에서 10.3${\sim}$1.18 정도였다. 같은 삼각형 범포 모형에서는 전자의 모형이 후자보다 $C_L$은 크게, 양항비는 작게 나타났다. 3. 모형에서 물의 유체력을 많이 받을 수 있는 곳에서 만곡꼭지점이 만들어지며, 삼각형 모형에서는 종횡비가 클수록, 역삼각형 모형에서는 작을수록 만곡꼭지점의 위치도 컸다. 4. 만곡도는 전 모형에서 종횡비가 클수록 컸으며, 삼각형 모형에서는 영각이 클수록 컸고 역삼각형 모형에서는 작을수록 컸다.

• 수산해양기술연구
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• 제38권3호
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• pp.234-240
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• 2002

본 연구에서는 전개판의 영각 변화에 따른 정적안정성에 관하여 이론적 해석을 하였다. 또한 전개판의 형상별 유체력에 의한 정적 안정성을 평가하기 위하여 종횡비가 다른 평판과 만곡도가 다른 종만곡판을 사용하여 회류수조에서 유체력 및 모벤트를 측정하고 형상별 압력중섬계수와 모멘트 계수를 계산하였다. 본 연구에서 얻어진 결과를 요약하면 다음과 같다. 1. 전개판의 영각($\alpha$) 변화에 따른 끌줄의 장력과 후릿줄의 장력에 의한 모멘트 변화는 전개판을 항상 정적 안정성을 가지도록 작용한다. 2. 종횡비(λ)가 0.5, 1.0, 1.5인 평판의 압력중심계 수는 영각의 증가와 함께 전연에서 중심쪽으로 이동한다. 이것은 유체력에 의한 모멘트는 항상 정적으로 안정하도록 작용한다는 것을 의미한다. 3. 종횡비가 일정(λ=1.5)하고, 만곡도(CR)가 5%, 10%, 15%, 20%인 만곡판의 유체력에 의한 압력중심계수는 영각의 증가와 함께 후연에서 전연쪽으로 이동한 다음, 다시 만곡판의 중심쪽으로 이동한다 만곡판에 작용하는 유체력에 의한 모멘트는 만곡도가 커질수록 정적으로 불안정한 영각의 범위가 증가한다.