• Wind and Structures
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• 제35권1호
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• pp.55-66
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• 2022

Tall buildings are often subjected to steady and unsteady forces due to external wind flows. Measurement and mitigation of these forces becomes critical to structural design in engineering applications. Over the last few decades, many approaches such as modification of the external geometry of structures have been investigated to mitigate wind-induced load. One such proven geometric modification involved the rounding of sharp corners. In this work, we systematically analyze the impact of rounded corner radii on the reducing the flow-induced loading on a square cylinder. We perform 3-Dimensional (3D) simulations for high Reynolds number flows (Re=1 × 105) which are more likely to be encountered in practical applications. An Improved Delayed Detached Eddy Simulation (IDDES) method capable of capturing flow accurately at large Reynolds numbers is employed in this study. The IDDES formulation uses a k-ω Shear Stress Transport (SST) model for near-wall modelling that prevents mesh-induced separation of the boundary layer. The effects of these corner modifications are analyzed in terms of the resulting variations in the mean and fluctuating components of the aerodynamic forces compared to a square cylinder with no geometric changes. Plots of the angular distribution of the mean and fluctuating coefficient of pressure along the square cylinder's surface illustrate the effects of corner modifications on the different parts of the cylinder. The windward corner's separation angle was observed to decrease with an increase in radius, resulting in a narrower and longer recirculation region. Furthermore, with an increase in radius, a reduction in the fluctuating lift, mean drag, and fluctuating drag coefficients has been observed.

• Journal of Advanced Marine Engineering and Technology
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• 제36권1호
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• pp.94-100
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• 2012

본 연구는 벽면 근처에 놓인 정방형주의 모서리에 수직 분할판을 부착하여 유체력 제어 효과를 양항력 측정실험 및 PIV에 의한 가시화 실험으로 조사한 것이다. 분할판의 폭은 정방형주 폭의 10% 로 했다. 실험변수로서는 수직 분할판의 부착 위치 및 벽면과 사각주 사이의 간격으로 하였다. 정방형주 중심에서 후류방향으로 3.0B(B: 정방형주 한 변 길이) 떨어진 곳에서 와도의 변화가 가장 명확했다. 수직 분할판의 위치 및 유무와 관계없이 간격비 0.4~0.6에서 평균양력계수 및 Strouhal 수의 변곡점이 나타났다. 정방형주 윗면의 뒷 모서리에 수직 분할판을 설치한 경우 항력이 감소하였으며 각 간격비 평균 5.0%의 항력 저감 효과를 얻었다. 정방형주 윗면 박리영역의 크기는 앞쪽 모서리에 수직 분할판을 설치한 경우가 가장 컸고, 원형의 정방형주, 뒷쪽 모서리에 수직 분할판을 설치한 순서로 작았으며, 평균항력계수는 이 박리영역의 크기에 비례했다.

• Wind and Structures
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• 제30권5호
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• pp.465-474
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• 2020

Vortex-induced vibrations of a yawed flexible cylinder near a plane boundary are numerically investigated at a Reynolds number Re_n= 500 based on normal component of freestream velocity. Free to oscillate in the in-line and cross-flow directions, the cylinder with an aspect ratio of 25 is pinned-pinned at both ends at a fixed wall-cylinder gap ratio G/D = 0.8, where D is the cylinder diameter. The cylinder yaw angle (α) is varied from 0° to 60° with an increment of 15°. The main focus is given on the influence of α on structural vibrations, flow patterns, hydrodynamic forces, and IP (Independence Principle) validity. The vortex shedding pattern, contingent on α, is parallel at α=0°, negatively-yawed at α ≤ 15° and positively-yawed at α ≥ 30°. In the negatively- and positively-yawed vortex shedding patterns, the inclination direction of the spanwise vortex rows is in the opposite and same directions of α, respectively. Both in-line and cross-flow vibration amplitudes are symmetric to the midspan, regardless of α. The RMS lift coefficient C_L,rms exhibits asymmetry along the span when α ≠ 0°, maximum C_L,rms occurring on the lower and upper halves of the cylinder for negatively- and positively-yawed vortex shedding patterns, respectively. The IP is well followed in predicting the vibration amplitudes and drag forces for α ≤ 45° while invalid in predicting lift forces for α ≥ 30°. The vortex-shedding frequency and the vibration frequency are well predicted for α = 0° - 60° examined.

• Selected Papers of The Society of Naval Architects of Korea
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• 제1권1호
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• pp.76-90
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• 1993

A new propeller series is developed using the newly developed blade section (KH 18 section) which has better cavitation characteristics and higher lift-drag ratio at wade angle-of-attack range than a conventional section. The radial patch distribution of the new series propellers is variable stance they were designed adaptively to a typical wake distribution. Basic geometric particulars of the series propellers. such as chord length, thickness, skew and rake distributions, are determined on the basis of recent full scale propeller geometric data. The series is developed for propellers having 4 blades, and blade area ratios of 0.3, 0.45, 0.6 and 0.75. Mean pitch ratios are varied as 0.5, 0.6, 0.7, 0.95 and 1.1 for each blade area ratio. The new propeller series consists of 20 propellers and is named as the KD(KRISO-DAEWOO)-propeller series. Propeller open-water tests are performed at the towing tank, and cavitation observation tests and fluctuating pressure tests are carried out at the cavitation tunnel of KRISO. $B_{p}-\delta$ curves, which can be used to select the optimum propeller diameter at the preliminary design stage, are derived from a regression analysis of the propeller open-water test results. The KD-cavitation chart is derived from the cavitation observation test results by choosing the local maximum lift coefficient and the local cavitation number as parameters. The cavity extent predicted by the KD-cavitation chart would be more accurate compared to that by an existing cavitation charts, such as the Burrll's cavitation chart, since the former is derived from the cavitation observation test results in a typical ship's wake, while the lather is derived from the test results in a uniform flow.

• 대한조선학회논문집
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• 제37권3호
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• pp.57-68
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• 2000

이착륙 속력을 줄이기 위해 날개 밑으로 프로펠러 후류를 불어넣어 날개와 수면사이의 압력을 증가시키는 PAR(Power Augmented Ram) 효과는 해면효과익선의 성능을 크게 향상시킨다. 본 논문에서는 풍동실험을 통해 이러한 PARWIG(Wing in Ground)선의 공력특성을 연구하였으며 송풍기(blower)와 덕트(duct)를 사용한 제트분사를 프로펠러 후류로 대신하였다. 제트의 분사속도, 분사위치(수평 및 수직 방향), 분사각 및 덕트 직경 변화에 대해 20인승 PARWIG선의 1/25 축소 모형선의 지면과의 고도, 앙각 및 플랩각의 변화에 따른 양력, 항력 및 피치모멘트를 계측하여 공력특성을 비교하였다. 적절한 PAR효과의 사용은 양력을 크게 증가시키며 최대 4의 양력계수까지 얻을 수 있었다.

• 한국항공우주학회지
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• 제38권7호
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• pp.637-646
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• 2010

포텐셜 기저 패널법과 시간전진법을 통합한 시간영역 패널법을 이용하여 융합익기 형상 초소형 무인기 FM07에 대한 정상/비정상 공력해석을 수행하였다. 융합익기 형상 무인기인 FM07의 공력해석에는 초기 설계형상(Case I)과 가로세로비를 증가시키고 무게중심을 후방으로 이동시킨 개선형상(Case II)이 사용되었다. 정상 공력해석을 통해 FM07 무인기의 개선형상이 초기형상에 비하여 보다 큰 양항비와 높은 피칭 안정성을 나타냄을 확인하였다. FM07의 비정상 급가속(발사체 이륙단계)을 나타낸 공력해석에서는 초기 급격한 증가를 보이는 공력계수들이 수초 후에 안정화되어 정상상태에 근사한 값을 나타내었다. FM07의 순항시 발생할 수 있는 피치진동운동에 대한 해석을 수행하여 진동에 따른 공력계수의 이력 현상을 확인하였으며, 개선형상이 보다 큰 민감도를 갖는 것을 확인하였다.

• 대한기계학회논문집B
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• 제36권5호
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• pp.465-475
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• 2012

본 연구는 두 가지 목표를 가지고 수행하였다. 하나는 수치해석과 Design-FOIL Pro.를 이용해 블레이드 에어포일 모델개발이고, 다른 하나는 이 모델을 Folding blade에 적용하는 것이다. 일반적으로 1MW이상 대형풍력터빈용 블레이드는 강풍시에 피칭제어로 풍향에 대해서 평형상태를 유지하여 로터를 회전시키지 않는 방법으로 블레이드의 손상을 방지 하였지만, 소형풍력터빈용 블레이드는 설비비, 유지비등 경제성을 이유로 피칭제어를 채택하지 않아 블레이드의 파손 문제가 심각하다. 그래서 본 연구에서는 유지보수가 필요 없고 강풍에서도 파손이 없는 Spring pack을 이용한 로터를 직접설계(Direct-Design) 방법으로 설계하여, 그 성능을 검증 하고 변화 풍속에 맞는 폴딩각을 이용해 강풍시에도 Wind turbine이 Cut-out 없이 계속발전을 유지할 수 있도록 하는 점에 집중 연구하고자 한다.

• Ocean Systems Engineering
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• 제4권3호
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• pp.185-200
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• 2014

The objective of the present simulations is to evaluate the applicability of the standard $k-{\varepsilon}$ turbulence model in engineering practice in the subcritical to supercritical flow regimes. Two-dimensional numerical simulations of flow around a circular cylinder at $Re=1{\times}10^5$, $5{\times}10^5$ and $1{\times}10^6$, had been performed using Unsteady Reynolds-Averaged Navier Stokes (URANS) equations with the standard $k-{\varepsilon}$ turbulence model. Solution verification had been studied by evaluating grid and time step size convergence. For each Reynolds number, several meshes with different grid and time step size resolutions were chosen to calculate the hydrodynamic quantities such as the time-averaged drag coefficient, root-mean square value of lift coefficient, Strouhal number, the coefficient of pressure on the downstream point of the cylinder, the separation angle. By comparing the values of these quantities of adjacent grid or time step size resolutions, convergence study has been performed. Solution validation is obtained by comparing the converged results with published numerical and experimental data. The deviations of the values of present simulated quantities from those corresponding experimental data become smaller as Reynolds numbers increases from $1{\times}10^5$ to $1{\times}10^6$. This may show that the standard $k-{\varepsilon}$ model with enhanced wall treatment appears to be applicable for higher Reynolds number turbulence flow.

• Advances in aircraft and spacecraft science
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• 제4권3호
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• pp.237-267
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• 2017

Automatic trajectory re-planning is an integral part of unmanned aerial vehicle mission planning. In order to be able to perform this task, it is necessary to dispose of formulas or tables to assess the flyability of various typical flight segments. Notwithstanding their importance, there exist such data only for some particularly simple segments such as rectilinear and circular sub-trajectories. This article presents an analysis of a new, very efficient, way for an airplane to fly on an inclined circular trajectory. When it flies this way, the only thrust required is that which cancels the drag. It is shown that, then, much more inclined trajectories are possible than when they fly at constant speed. The corresponding equations of motion are solved exactly for the position, the speed, the load factor, the bank angle, the lift coefficient and the thrust and power required for the motion. The results obtained apply to both types of airplanes: those with internal combustion engines and propellers, and those with jet engines. Conditions on the trajectory parameters are derived, which guarantee its flyability according to the dynamical properties of a given airplane. An analytical procedure is described that ensures that all these conditions are satisfied, and which can serve for producing tables from which the trajectory flyability can be read. Sample calculations are shown for the Cessna 182, a Silver Fox like unmanned aerial vehicle, and an F-16 jet airplane.

• 한국가시화정보학회지
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• 제21권2호
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• pp.83-90
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• 2023

The shape of an airfoil is a critical factor in determining aerodynamic characteristics such as lift and drag. Aerodynamic properties of an airfoil have a decisive impact on the performance of various engineering applications, including airplane wings and wind turbine blades. Therefore, it is essential to analyze the aerodynamic characteristics of airfoils. Various analytical tools such as experiments, computational fluid dynamics, and Xfoil are used to perform these analyses, but each tool has its limitation. In this study, airfoil parameterization, image recognition, and artificial intelligence are combined to overcome these limitations. Image and coordinate data are collected from the UIUC airfoil database. Airfoil parameterization is performed by recognizing images from image data to build a database for deep learning. Trained model can predict the aerodynamic characteristics not only of airfoil images but also of sketches. The mean absolute error of untrained data is 0.0091.