• 오토저널
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• 제14권6호
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• pp.39-47
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• 1992

The engine combustion is one of the most important process affecting performance and emissions. One effective way to improve the engine combustion is to control motion of the charge inside a cylinder by means of optimum induction system design, because the flame speed is mainly determined by the turbulence in a gasoline engine. This paper describes the measurement and characterization of mean velocity and turbulence intensity inside the cylinder of a 4-valve gasoline engine using laser Doppler velocimeter(LDV) under motoring(non-firing) conditions. Since the measured LDV data in each cycle show small cycle variation during compression stroke in the tested engine, the mean velocity and turbulence intensity are calculated by ensemble averaging method neglecting cycle variation effects. In the ensemble averaging method, the effects of the calculation window, in which velocities are assumed as the same crank angle, on mean velocity and turbulence intensity are fully investigated. In addition, the effects of measuring point on the flow characteristics are studied. With large calculation window, the mean velocity is shown to be less sensitive with respect to crank angle and turbulence intensity decrease in its absolute amplitude. When the piston approch to the top dead center of compression, the turbulence intensity is found to be homogeneous in the cylinder.

• 대한기계학회논문집
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• 제18권4호
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• pp.920-932
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• 1994

The combustion phenomena of a reciprocating engine is one of the most important processes affecting performance and emissions. One effective way to improve the engine combustion is to control the motion of the charge inside a cylinder by means of optimum induction system design, because the flame speed is mainly determined by the turbulence at compression(TDC) process in S.I. engine. It is believed that the tumble and swirl motion generated during intake breaks down into small-scale turbulence in the compression stroke of the cycle. However, the exact nature of their relationship is not well known. This paper describes cycle resolved LDV measurement of turbulent flow inside the cylinder of a 4-valve engine under motoring(non-firing) conditions, and studies the effect of intake port configurations on the turbulence characteristics using following parameters ; Eulerian temporal autocorrelation coefficient, turbulence energy spectral density function, Taylor micro time scale, integral time scale, and integral length scale.

• Journal of Advanced Marine Engineering and Technology
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• 제32권4호
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• pp.498-505
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• 2008

Many researches have been studied on in-cylinder flow as one of dominant effects for an engine combustion. The combustion phenomena of reciprocating engine is one of the most important processes affecting performance and emissions. One effective way to improve the engine combustion is to control the motion of the charge inside a cylinder by means of optimum induction system design. It is believed that the tumble and swirl motion generated during intake breaks down into small-scale turbulence in the compression stroke of the cycle. However, the exact nature of their relationship is not well known. To know this relationship definitely, this paper describes analytical results of the tumble motion, swirl motion, turbulence intensity, turbulence inside the cylinder of marine engine. 3-D computation has been performed by using STAR-CD solver and es-ice.

• 한국항공운항학회지
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• 제29권3호
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• pp.34-43
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• 2021

Wake turbulence generated by the lead aircraft has a significant impact on the following aircraft and it is has been considered a key factor to consider whenin determining the longitudinal separation between the aircraft. ICAO classifies aircraft into four wake turbulence categories based on the maximum takeoff weight and provides the longitudinal separation minima for each category. Due to richer measured data and better understanding of physical processes, it is raised that classifying aircraft with only four wake turbulence grades is imprecise and leads to over-separation in many instances. In this regards, much research on a new method of classifying Wake Turbulence Category(Re-CAT) has been done by EURO-CONTROL, FAA, and ICAO. The main purpose of this study is to conduct a comparative analysis of the existing wake turbulence separation standards with Re-CAT in terms of departure capacity and the resulting benefits of Re-CAT using the data from the Incheon International Airport. The results show that EUROCONTROL and new ICAO standards have the greater effect on reducing wake turbulence separation, compared to the FAA RE-CAT standards. It is also concluded that Re-CAT presents different results of wake turbulence separation depending on the flight characteristics of each airport.

• 대한기계학회논문집A
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• 제34권12호
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• pp.1885-1891
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• 2010

풍력터빈의 토크제어는 정격풍속 이하에서 매우 중요하다. 토크제어의 주된 목적은 바람이 가진 공기역학적 파워로부터 최대의 파워를 얻도록 하는 것이다. 풍력터빈의 토크제어 방법은 토크모드 제어와 속도모드 제어로 크게 두 경우로 구분된다. 토크모드 제어는 풍력터빈에서 잘 알려지고 전통적으로 사용되는 방법으로 발전기 회전속도의 제곱에 비례하도록 발전기의 토크크기를 발생시킨다. 속도모드 제어에서는 발전기의 토크크기를 발생하기 위하여 PI 제어기를 사용한다. 본 논문에서는 실제 풍속이 난류인 점을 고려하여 2.75 MW 풍력터빈을 대상으로 두 토크제어 방법을 적용한 수치실험 결과를 제시하고 응답특성을 비교한다.

• 한국전산유체공학회지
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• 제11권3호
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• pp.59-63
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• 2006

Accurate prediction of a supersonic missile base drag continues to defy even well-rounded CFD codes. In an effort to address the accuracy and predictability of the base drags, the influence of grid system and competitive turbulence models on the base drag is analyzed. Characteristics of some turbulence models is reviewed through incompressible turbulent flow over a flat plate, and performance for the base drag prediction of several turbulence models such as Baldwin-Loman(B-L), Spalart-Allmaras(S-A), k-$\varepsilon$, k-$\omega$ model is assessed. When compressibility correction is injected into the S-A model, prediction accuracy of the base drag is enhanced. The NSWC wind tunnel test data are utilized for comparison of CFD and semi-empirical codes on the accuracy of base drag predictability: they are about equal, but CFD tends to perform better. It is also found that, as angle of attack of a missile with control fins increases, even the best CFD analysis tool we have lacks the accuracy needed for the base drag prediction.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 The Fifth Asian Computational Fluid Dynamics Conference
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• pp.39-41
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• 2003

n this paper, direct numerical simulation of decaying compressible turbulence with passive scalar is performed by using 7th order upwind difference scheme or 8th order group velocity control scheme. The start Reynolds number (defined by Taylor scale) is 72 and turbulent Mach numbers are 0.2-0.9. The Schmidt numbers of passive scalar are 2-10. The Batchelor k-1 range are found in scalar spectra, and the high wavenumber spectra decays faster with increasing turbulent Mach number. The extend self-similarity (ESS) is found in the passive scalar in compressible turbulence.

• Ocean Systems Engineering
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• 제8권3호
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• pp.281-312
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• 2018

Characteristics of a turbulence wind model control the magnitude and frequency distribution of wind loading on floating offshore wind turbines (FOWTs), and an in-depth understanding of how wind spectral characteristics affect the responses, and ultimately the design cost of system components, is in shortage in the offshore wind industry. Wind spectrum models as well as turbulence intensity curves recommended by the International Electrotechnical Commission (IEC) have characteristics derived from land-based sites, and have been widely adopted in offshore wind projects (in the absence of site-specific offshore data) without sufficient assessment of design implications. In this paper, effects of wind spectra and turbulence intensities on the strength or extreme responses of a 5 MW floating offshore wind turbine are investigated. The impact of different wind spectral parameters on the extreme blade loads, nacelle accelerations, towertop motions, towerbase loads, platform motions and accelerations, and mooring line tensions are presented and discussed. Results highlight the need to consider the appropriateness of a wind spectral model implemented in the strength design of FOWT structures.

• 한국광학회지
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• 제31권6호
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• pp.247-258
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• 2020

본 논문에서는 대기외란에 따른 SPGD 위상제어 알고리즘 기반 결맞음 빔결합 시스템의 위상제어 동작성능을 논의한다. 대기의 외란에 대한 통계적 이론을 바탕으로 전산모사를 통해 대기외란에 의한 레이저빔의 위상 및 파면 왜곡에 대한 분석과 왜곡된 빔을 통해 얻게 되는 7채널 및 19채널 결맞음 빔결합 결과를 도출하고, 이를 통해 대기외란의 정도에 따른 빔결합 시스템의 위상제어 동작성능 및 효율을 수치적으로 비교분석한다. 분석 결과, 7채널 결맞음 빔결합의 경우, 대기외란 파라미터 cn2 값이 10-13 m-2/3 까지 증가한 상황에서도 SPGD 위상제어 알고리즘을 적절히 적용할 경우 90% 이상의 빔결합 효율로 시스템의 위상 잠금이 가능하다는 것을 확인하였다. 19채널 결맞음 빔결합의 경우, 동일한 대기외란 조건에서도 대기의 굴절률 비균질성(refractive index inhomogeneity)의 영향이 더 커서 빔결합 효율이 60% 수준으로 급격하게 감소할 수 있음을 확인하였다. 또한, 대기외란이 있는 상황에서 위상잠금시점까지 요구되는 알고리즘의 반복연산 횟수와 대기현상의 변화간격을 비교분석함으로써, 다채널 결맞음 빔결합 시스템이 ㎲의 간격을 가지는 대기외란 상황에서도 정상동작을 하기 위해서는 SPGD 위상제어 알고리즘의 연산대역폭이 수백 MHz에서 수 GHz까지 확장되어야 한다는 것을 확인하였다. 향후, 대기외란이 SPGD 위상제어 알고리즘 기반 결맞음 빔결합 시스템의 위상제어 동작성능에 미치는 영향을 정량적으로 분석하고 예측하는 데 있어서 본 논문의 결과가 유용하게 활용될 수 있을 것이라 기대된다.

• Wind and Structures
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• 제32권3호
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• pp.205-217
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• 2021

Cold regions with high air density and wind speed attract wind energy producers across the globe exhibiting its potential for wind exploitation. However, exposure of wind turbine blades to such cold conditions bring about devastating impacts like aerodynamic degradation, production loss and blade failures etc. A series of wind tunnel tests were performed to investigate the effect of icing on the aerodynamic properties of wind turbine blades. A baseline clean wing configuration along with four different ice accretion geometries were considered in this study. Aerodynamic force coefficients were obtained from the surface pressure measurements made over the test model using MPS4264 Simultaneous pressure scanner. 3D printed Ice templates featuring different ice geometries based on Icing Research Tunnel data is utilized. Aerodynamic characteristics of both the clean wing configuration and Ice accreted geometries were analysed over a wide range of angles of attack (α) ranging from 0° to 24° with an increment of 3° for three different Reynolds number in the order of 105. Results show a decrease in aerodynamic characteristics of the iced aerofoil when compared against the baseline clean wing configuration. The key flow field features such as point of separation, reattachment and formation of Laminar Separation Bubble (LSB) for different icing geometries and its influence on the aerodynamic characteristics are addressed. Additionally, attempts were made to understand the influence of Reynolds number on the iced-aerofoil aerodynamics.