• 한국해안해양공학회지
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• 제10권2호
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• pp.83-92
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• 1998

대격자망 수치모형에서 저항물체에 의한 유수저항을 평가하기 위하여, 항력으로부터 유도된 drag stress를 수심적분된 Reynolds 방정식에 도입하였다. 그리고, 해석해가 존재하는 조건에 대한 다양한 수치실험을 통하여 본 모형의 적용성 및 문제점을 검토하였다. 단일물체의 경우, 수치해는 해석해에 대하여 유속의 크기에 있어서$\pm$10% 정도의 오차범위를 나타내는 좋은 일치를 보였으며 후류폭의 크기도 전 경우에 있어서 해석해와 잘 일치 하였다. 또한, 열을 이룬 물체에 대한 항력계수와 와동점성계수가 정확하게 결정된다면, 본 모형은 열을 이룬 물체 배후에서 평균류의 흐름분포를 평가하는 데 효율적으로 이용될 수 있을 것이다.

• 한국농공학회지
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• 제35권4호
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• pp.76-85
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• 1993

The purpose of this study was to analyze the wind force distribution on the two single-span arched plastic house depending upon the house spacing and wind direction, which may provide the fundamental criteria for the structural design. In order to specify the wind force distribution, the variation of the wind force coefficients, the mean wind force coefficients and the drag force coefficients were estimated from the wind tunnel test data. The results obtained are as follows : 1. At the wind direction of 90$^{\circ}$, there was a typical span interval at which the maximum negative pressure was occured at the edge of the inside walls. 2. In the consideration of wind loads, the wind force coefficients estimated from independent single-span arched plastic house should not be directly applied to the structural design on the double houses separated. 3. The average maximum negative wind force on the inside walls was occured at the wind direction of 90$^{\circ}$, and the variations depending on the span intervals was not significant. 4. The average maximum drag force was occured at the wind direction of 300, and the magnitude of drag force was more significant at the first house. As the distance between two houses was increased, the drag force was slightly increased for every wind direction.

• 한국가시화정보학회지
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• 제9권2호
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• pp.40-47
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• 2011

Tilt-rotor aircraft can be used in various fields because they have the capabilities of the vertical take-off and landing and the high-speed cruise flight. In the present study, the flow analysis of a tilt-rotor aircraft is conducted at various tilt angles. The lift and drag forces of the tilt-rotor aircraft are obtained and the wakes by the rotor-blade are visualized. The result shows that the rotor-blade affects the lift force in a hovering mode and the main wing has an influence on the lift force in a cruise mode. Additional thrust is required at the tilt angle of around 40 degree due to the least lift force. The drag force is dependent on the rotor-blade at overall tilt angles. The minus drag force appears between the tilt angles of 90 degree and 55 degree. Also, the drag force is dramatically increased at the other tilt angles. The wake by rotor-blade affects the flow around the fuselage of the tilt-rotor aircraft at the tilt angles of 75 degree and 60 degree.

• 한국자동차공학회논문집
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• 제10권2호
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• pp.87-95
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• 2002

The aim of this article is to perform the numerical simulation far drop drag and breakup processes in air-assisted sprays using the Taylor analogy breakup (TAB) model with a modified drop drag model, in which a random method is newly used to consider the variation of the drop's frontal area. The predicted results for drop trajectory and Salter mean diameter (SMD) were compared with experimental data and the simulation results using the earlier published models such as TAH model, surface wave instability (Wave) model, and Wave model with original drop drag model. In addition, the effects of the breakup model constant, Ck, on prediction of spray behaviors were discussed. The results shows that the TAB model with the modified drop drag model is in better agreement with experimental data than the other models, indicating the present model is acceptable for predicting the drop breakup process in air-assisted sprays. At higher Weber numbers, the smaller Ck shows the best fitting to experimental data. It should be noted that more elaborated studies is required in order to determine the breakup model constant in the suggested model in the study.

• Applied Science and Convergence Technology
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• 제25권6호
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• pp.120-123
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• 2016

The rotor of a turbomolecular drag pump is generally made of an aluminum alloy. Its surface finish is affected by various processes that the rotor itself undergoes during the manufacturing phase. The impact of different surface finishes on the pumping performances of a turbomolecular pump has been mainly investigated by Sawada et al [1]. The present work aims to broaden the previous bibliographic study to the drag stages of a turbomolecular pump by testing the impact of different surface finishes on the compression ratio of the pump. Experimental tests have been made focusing on two processes: the corundum sandblasting and the glass microspheres shot-peening. Both the processes flatten and/or physically remove EDM melted spheres; in particular, blasted surfaces obtained by glass shot-peening are generally smoother than surfaces obtained by corundum sandblasting. In order to characterize the surface texture left by such processes, preliminary surface roughness measurements have been made on the drag rotor disks of several pumps. The experimental tests conducted on both sandblasted and shot-peened rotors confirms previous results obtained on the turbo stages by Sawada et al. [1], showing that the average roughness of the surface has an impact on the compression ratio of the pump; in particular, an increment in the surface roughness causes a corresponding increment in the compression ratio of the pump and vice versa. For the tested pumps, the higher surface roughness gives a factor of increment of about 2 on the measured hydrogen maximum compression ratio of the pump.

• 항공우주기술
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• 제5권2호
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• pp.205-212
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• 2006

고도 800km 이내의 저궤도 위성에 가장 큰 영향을 주는 요소는 지구 대기 항력이다. 지구 저궤도의 대기 밀도는 해수면의 대기 밀도에 비하여 매우 낮지만 항력에 의한 영향이 매 주기 마다 누적되면서 근지점에서 속도가 점진적으로 줄어든다. 근지점에서의 속도 감소는 곧바로 원지점의 고도 감소를 가져오게 되고 이심률이 작아지면서 최종적으로 원궤도로 바뀌게 된다. 본 논문에서는 이러한 대기 항력 및 수명 계산 방법에 대하여 기술하였다. 또한 항력의 크기를 결정하는 대기 밀도에 관해서 알아보고 KSLV-I에 사용될 킥모터와 위성의 수명을 Satellite Tool Kit 프로그램으로 계산하였다.

• Journal of Advanced Marine Engineering and Technology
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• 제31권5호
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• pp.552-557
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• 2007

This paper has dealt with the effect of non ionized surfactant and water mixture on drag reduction and heat transfer enhancement in a circular pipe flow with experimentally. The test section was consisted of stainless steel pipe with inside diameter of 16mm. The wire coil was used to increase heat transfer in a pipe and the on ionized surfactant(Oleyl Dihydroxyethyl Amino Oxide, ODEAO) was used to reduce the drag force of water mixture with surfactant. The main parameters of this experiment were diameter and pitch of wire coil and the ratio of test section length and horizontal wire coil length. In this experiment, the acquired results were 1) Drag reduction effect existed in this ODEAO-water mixture, 2) Friction factor and heat transfer were increased with insertion the heat transfer enhancement coil, 3) With increasing of pitch ratio, heat transfer was decreased, and 4) Heat transfer was decreased by the decreasing of inserting coil diameter.

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2003년도 춘계학술대회 논문집
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• pp.49-55
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• 2003

When a body with slant angle after its shoulder is moving at high speed, the turbulent motion around the afterbody is generally associated with the flaw separation and determines the normal component of the drag. By changing the slant angle of afterbody, there exists a critical angle at which the drag coefficients change drastically. Understanding and control of the turbulent separated flows are of significant importance for the design of optimal configuration of the moving bodies. In the present paper, a new Large Eddy Simulation technique has been developed to investigate turbulent vortical motions around the afterbodies with slant angle. By basis of understanding the structure of turbulent flaw around the body, the new configuration of afterbodies are designed to reduce the drag of body and the nonlinear effects due to the interaction between the body configuration and the turbulent separated flows are investigated by use of the developed LES technique.

• 한국군사과학기술학회지
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• 제22권6호
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• pp.773-783
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• 2019

A numerical analysis of a turbulent flow with a 'large-eddy breakup device(LEBU)' was performed to investigate the influence of the device on the drag of underwater vehicle using commercial CFD code, FLUENT. In the present study, the vehicle drag was decomposed to skin-friction coefficient(C_f) and pressure coefficient(C_p). The variation of the vehicle C_f and C_p were observed with changing location of the device and Reynolds number. As a result, the device decreased the vehicle C_f because it suppressed the turbulent characteristics behind the device. The larger Reynolds number, the higher reduction effect when the device was placed in front part of, and near the vehicle. On the other hand, the device increased/decreased the vehicle C_p with increasing/decreasing turbulent kinetic energy at recirculating flow region behind the vehicle. The total drag change by the device was caused by C_p rather than C_f.

• 대한조선학회논문집
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• 제31권3호
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• pp.100-111
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• 1994

고속정은 spray를 수반하는 흐름 특성을 가지고 있다. 본 연구에서는 이러한 spray의 흐름 특성을 파악하기 위해 몇가지 실험을 수행하였다. 우선 아크릴판으로 만든 주상활주선형을 이용하여, 예인수조에서 흐름의 가시화를 수행하고, 그 기록으로부터 화상해석을 통하여 spray흐름의 방향, 유속등을 계측하였다. Spray에 의해 발생하는 모델의 양력, 항력을 구하기 위해서는 spray의 두께가 주요한 계측 항목이 된다. 본 연구에서는 운동량 이론을 이용한 새로운 spray의 두께 계측법을 제시하였다. Spray의 두께를 국부적으로 계측하여 저항성분을 구하여 적분하므로써, 본 실험모델이 받는 저항성분중 spray저항을 평가하였다. 또한 활주모델의 저면에서 압력을 계측하여 spray가 발생하는 원리를 보여 주었으며, 계측된 압력을 적분하므로써 모델에 작용하는 압력저항성분을 평가하였다.