• Journal of Ship and Ocean Technology
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• 제8권2호
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• pp.13-19
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• 2004

Jet flows applied tangential to a foil surface near the leading and/or trailing edges increase the lift of the foil by delaying the separation also known as the Coanda effects. Many experimental and numerical studies have proven the effectiveness of Coanda effects on circulation control and the effects have been found to be useful in practical application in many aerodynamics fields. Most of the previous works have studied the effects of the jet blowing near the trailing edges and investigated the influence of jet momentum on lift. A few experimental studies, however, focused on the separation bubble that develops near the leading edge and applied jet flow the edge to remove the bubble but only to find decrease in lift. In the present paper, a Coanda foil of 20% thickness ellipse with modified rounded leading and trailing edges was investigated, and the flow around the foil was numerically studied. The blowing around the leading edge only decreased the lift, as the experiments showed, but the suction considerably increased the lift.

• 한국전산유체공학회지
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• 제19권4호
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• pp.75-79
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• 2014

In the paper, a study on the analysis of the effects of trailing edge thickness on the aerodynamic characteristics of an airfoil is described. In this research, modification of the formula representing NACA symmetric airfoil is studied to change the airfoil shape with different trailing edge thickness of user's choice. According to the result of aerodynamic characteristics, as the trailing edge thickness increases the maximum lift coefficient increases while the lift-to-drag ratio decreases. In this paper flow calculation results are demonstrated and the analysis on those results and findings on the effects of non-zero thickness of trailing edge are suggested.

• Structural Engineering and Mechanics
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• 제3권3호
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• pp.229-244
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• 1995

The parametric instability behaviour of a plate subjected to localized in-plane compressive or tensile periodic edge loading is studied, considering the effects of damping into the system. Different edge loading cases have been considered. Damping has been introduced in the form of proportional damping. Dynamic instability behaviour under compressive or tensile periodic edge loading shows that the instability regions are influenced by the load band width and its location on the edge. The effects of damping on the instability regions show that there is a critical value of dynamic load factor beyond which the plate becomes dynamically unstable. The critical dynamic load factor increases as damping increases. Damping generally reduces the widths of the instability regions.

• 한국정밀공학회지
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• 제16권7호
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• pp.188-195
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• 1999

Cutting edge plays an important role in generating machined surface. In order to consider the geometric effects of the cutting edge on mechanical states, the concept of ploughing force and stagnation point was introduced which explains the generating mechanism of machined surface during cutting. The effects of edge radius and nose radius of cutting tool on the distribution of residual stresses of the machined surface having several hardness were studied. Good machined surface having high compressive residual surface stresses can be achieved if cutting tools having large edge radius and small nose radius are used for cutting work materials having high hardness with high depth of cut. The magnitude of edge radius and the hardness of work material also affected the shape of the chip in orthogonal cutting.

• Steel and Composite Structures
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• 제29권5호
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• pp.681-688
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• 2018

In this paper, buckling load of edge stiffened composite plates is assessed. The effect of stiffener edge size, circular hole, and the fiber orientation angle on buckling behavior of composite plates under uni-axial compressive load is investigated. This paper includes two parts as experimental and numerical studies. L-shape composite plates are manufactured in three different layups. Then the buckling loads are experimentally determined. Subsequently, by using the numerical simulation, the size variation effects of stiffener edge and circular cutout on the plate buckling loads are analyzed in five different layups. The results show that cutout size, stiffener edge height and fiber orientation angle have important effects on buckling load. In addition, there is an optimum height for stiffener edge during different conditions.

• 한국연소학회지
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• 제14권1호
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• pp.1-8
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• 2009

Experiment is conducted to grasp effects of flame curvature on flame behavior in laminar lifted-jet flames. Nozzle diameters of 0.1 and 1.0mm are used to vary flame curvature of edge flame. There exist three types of edge flame oscillation. These edge flame oscillations may be caused by radial heat loss at all flame conditions, by fuel Lewis numbers near or larger than unity with the help of appreciable radial conduction heat loss, and by buoyancy effects. These are confirmed by the analysis of oscillation frequencies. It is however seen that the change of lift-off height through edge-flame oscillation is mainly due to radial heat loss irrespective of Lewis number and buoyancy.

• 한국멀티미디어학회논문지
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• 제8권12호
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• pp.1565-1571
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• 2005

Images reconstructed with Maximum-Likelihood Expectation-Maximization (MLEM) algorithm have been observed to have checkerboard effects and have noise artifacts near edges as iterations proceed. To compensate this ill-posed nature, numerous penalized maximum-likelihood methods have been proposed. We suggest a simple algorithm of applying edge detecting process to the MLEM and Bayesian Expectation-Maximization (BEM) to reduce the noise artifacts near edges and remove checkerboard effects. We have shown by simulation that this algorithm removes checkerboard effects and improves the clarity of the reconstructed image and has good properties based on root mean square error (RMS).

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2001년도 유체기계 연구개발 발표회 논문집
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• pp.149-155
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• 2001

Recently, it is required to design higher stage pressure ratio compressor while maintaining equal adiabatic efficiency. To increase the stage pressure ratio, blade rotational speed or diffusion factor should be increased. In the case of increasing rotational speed, relative speed of flow at blade leading edge is well supersonic. In supersonic blade, total pressure loss is mainly due to shock wave and blade leading edge thickness should be very thin to minimize the shock wave loss. As a result, the blade is like to be week in terms of mechanical strength and the manufacturing cost is very high because NC machining is necessary. It is also one of big hurdle to overcome to make small compressor. In this paper, the effects of blade leading edge to the performance of supersonic blade In terms of total pressure loss. The efficiency of already known method to make thin blade leading edge from the casted blade with rather thick leading edge thickness is also assessed.

• 한국항공우주학회지
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• 제35권10호
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• pp.899-904
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• 2007

전투기급 항공기 개념설계 기간 중 항공기 초음속 순항성능에 미치는 앞전플랩 굽힘 효과를 분석하기 위하여 1/20 축척 날개-동체-꼬리 형상 모형을 사용한 고속 풍동시험을 수행하였다. 풍동시험을 위한 적절한 앞전플랩 각도를 선정하기 위하여 보정된 초음속 패널 방법을 사용하여 다양한 앞전플랩 굽힘 각도에 따른 공력특성을 분석하였다. 실험 및 수치해석적 접근 결과 분석을 기초로, 앞전플랩 굽힘 효과는 전투기급 항공기의 초음속 순항 성능 증대에 유용한 것으로 확인되었다.

• 한국산학기술학회논문지
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• 제14권2호
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• pp.511-516
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• 2013

유리 모서리 접합은 디스플레이 및 건축, 가전 등 산업계의 다양한 분야에 활용되고 있으며, 패널 접합부의 두께 및 형상은 단열성능 및 강도 등 패널의 주요 성능에 큰 영향을 미치는 요인으로 작용한다. 이런 모서리 접합부의 단면은 수소혼합가스토치를 이용하여 모서리를 용융 접합 할 경우 공정변수에 의해 형상이 결정된다. 따라서 본 논문에서는 가스토치를 이용하여 모서리 접합 시 접합부에 영향을 미치는 공정변수를 설정하고, 접합단면의 형상변수를 설정하여 두 변수간의 상관관계를 분석하기 위한 회귀식을 도출하고자 하였다. 회귀식 도출을 위해 공정변수가 형상변수에 미치는 주효과 및 교호작용을 분석하였으며, 변수간의 교호작용을 고려한 다항회귀식을 도출하였다. 도출된 다항회귀식을 통해 각 공정변수 변화에 따라 모서리 접합 두께 예측 및 처짐량 예측이 가능하다.