• 대한기계학회논문집B
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• 제32권7호
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• pp.549-557
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• 2008

Despite of the laminar-turbulent transition region co-exist with fully turbulence region around the leading edge of an airfoil, still lots of researchers apply to fully turbulence models to predict aerodynamic characteristics. It is well known that fully turbulent model such as standard k-model couldn't predict the complex stall and the separation behavior on an airfoil accurately, it usually leads to over prediction of the aerodynamic characteristics such as lift and drag forces. So, we apply correlation based transition model to predict aerodynamic performance of the NREL (National Renewable Energy Laboratory) Phase IV wind turbine. And also, compare the computed results from transition model with experimental measurement and fully turbulence results. Results are presented for a range of wind speed, for a NREL Phase IV wind turbine rotor. Low speed shaft torque, power, root bending moment, aerodynamic coefficients of 2D airfoil and several flow field figures results included in this study. As a result, the low speed shaft torque predicted by transitional turbulence model is very good agree with the experimental measurement in whole operating conditions but fully turbulent model(${\kappa}-\;{\varepsilon}$) over predict the shaft torque after 7m/s. Root bending moment is also good agreement between the prediction and experiments for most of the operating conditions, especially with the transition model.

• Wind and Structures
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• 제26권5호
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• pp.331-341
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• 2018

A numerical study on the flow over a square cylinder in the vicinity of a wall is conducted for different Couette-Poiseuille-based non-uniform flow with the non-dimensional pressure gradient P varying from 0 to 5. The non-dimensional gap ratio L (=$H^{\ast}/a^{\ast}$) is changed from 0.1 to 2, where $H^{\ast}$ is gap height between the cylinder and wall, and $a^{\ast}$ is the cylinder width. The governing equations are solved numerically through finite volume method based on SIMPLE algorithm on a staggered grid system. Both P and L have a substantial influence on the flow structure, time-mean drag coefficient ${\bar{C}}_D$, fluctuating (rms) lift coefficient ($C_L{^{\prime}}$), and Strouhal number St. The changes in P and L leads to four distinct flow regimes (I, II, III and IV). Following the flow structure change, the ${\bar{C}}_D$, $C_L{^{\prime}}$, and St all vary greatly with the change in L and/or P. The ${\bar{C}}_D$ and $C_L{^{\prime}}$ both grow with increasing P and/or L. The St increases with P for a given L, being less sensitive to L for a smaller P (< 2) and more sensitive to L for a larger P (> 2). A strong relationship is observed between the flow regimes and the values of ${\bar{C}}_D$, $C_L{^{\prime}}$ and St. An increase in P affects the pressure distribution more on the top surface than on bottom surface while an increase in L does the opposite.

• Wind and Structures
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• 제35권2호
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• pp.83-92
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• 2022

When the rolling stocks run on the curve, the external rail has to be lifted to a certain level to balance the centrifugal force acting on the train body. Under such a situation, passengers may feel uncomfortable, and the slanted vehicle has the potential overturning risks at high speed. This paper conducted a wind tunnel test in an annular wind tunnel with φ=3.2 m based on a 1/20^th scaled high-speed train (HST) model. The sensitivity of Reynolds effects ranging from Re = 0.37×10⁶ to Re = 1.45×106 was tested based on the incoming wind from U=30 m/s to U=113 m/s. The wind speed covers the range from incompressible to compressible. The impact of roll angle ranging from γ=0° to γ=4° on train aerodynamics was tested. In addition, the boundary layer development was also analyzed under different wind speeds. The results indicate that drag and lift aerodynamic coefficients gradually stabilized and converged over U=70 m/s, which could be regeared as the self-similarity region. Similarly, the thickness of the boundary layer on the floor gradually decreased with the wind speed increase, and little changed over U=80 m/s. The rolling moment of the head and tail cars increased with the roll angle from γ=0° to γ=4°. However, the potential overturning risks of the head car are higher than the tail car with the increase of the roll angle. This study is significant in providing a reference for the overturning assessment of HST.

• 대한기계학회논문집A
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• 제38권6호
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• pp.609-617
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• 2014

풍력터빈 블레이드의 가변 피치제어는 풍력발전기의 과풍속 영역 설계에 있어 중요한 요소로 알려져 있으나 원가문제 때문에 소형 풍력터빈에는 적용되지 못하고 실속제어가 많이 적용되고 있다. 하지만, 블레이드 주변의 난류 때문에 설계된 실속이 구현되지 않는 실속지연 현상이 종종 발생되고, 이에 따른 풍력 블레이드의 과회전과 발전기의 과출력 위험이 발생하고 있다. 이에 따라 블레이드에서 발생되는 공력으로 피치가 변하고 스프링의 복원력으로 복귀되는 수동형 피치제어 모듈이 주목 받고 있다. 본 연구에서는 회전하는 블레이드의 익형에서 발생되는 양력과 항력을 이용하여 회전면으로 작용되는 토크와 블레이드의 Flap 방향으로 작용되는 추력을 계산하는 방법을 제시하고, 이러한 힘들의 크기를 여러 가지 익형에 대해 비교하였으며, 블레이드의 피치모멘트를 정량적으로 산출하여 수동 피치제어 모듈의 설계자료로 활용될 수 있도록 하였다.

• 한국항공우주학회지
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• 제42권7호
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• pp.535-543
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• 2014

비세장형, 둥근 앞전을 가지고 스팬이 1.0m로 축소된 BWB형 UCAV에 대해 완전난류, 천이 모델을 사용하여 전산해석을 수행하였다. 자유류는 받음각 -4도부터 26도까지 50m/s이며, 평균 시위 기준 레이놀즈수는 $1.25{\times}10^6$이다. 멀티블록 6면체 격자와 함께 완전난류 모델과 천이 모델의 결과를 비교하여 천이효과가 공력 특성에 미치는 영향을 살펴보았다. 풍동 실험과 비교한 결과 양/항력 계수는 해석범위 내에서 잘 일치하였으며, 피칭 모멘트는 높은 받음각에서 작게 예측됨과 동시에 난류모델에 따라 결과가 크게 달라졌다. 압력분포와 skin friction line, 축 방향 속도장을 이용하여 와류구조의 거동과 천이현상이 미치는 영향을 살펴본 결과, 천이효과를 고려하는 것이 UCAV의 정확한 와류 구조와 공력특성 예측에 필요한 것으로 확인하였다.

• 한국항공우주학회지
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• 제34권5호
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• pp.1-11
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• 2006

본 연구에서는 연속적 블로잉 요소들의 변화가 낮은 레이놀즈 수를 가지는 유동장에서 NACA 0015 익형 주위의 유동제어 및 익형의 실속제어에 미치는 영향에 대하여 비정렬 격자계를 사용하는 수치적 기법을 이용하여 살펴보았다. 실속 이전의 받음각들에서 연속적 블로잉 요소들의 변화에 따른 공력계수 및 모멘트 계수의 변화를 통하여 각 요소들의 유동제어 효과를 살펴보았으며, 각 요소들의 변화에 따른 실속각의 변화를 통하여 실속제어 효과를 살펴보았다. 실속이전의 받음각에서 비교적 강한 세기의 블로잉을 수행하면 항력의 증가를 동반한 양력의 증가가 나타났다. 앞전부근에서의 적절한 세기의 연속적 블로잉은 실속이전의 각에서 양력의 증가를 나타내고, 실속제어 특성을 보였다. 블로잉 제트의 방향이 유동제어를 하지 않았을 때의 블로잉 슬롯 주변 유동의 방향과 일치하는 경우가 가장 좋은 유동제어 특성을 나타냄을 알 수 있었다.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.8-16
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• 2017

Most of small air vehicles with moving wing fly at low Reynolds number condition and the reduced frequency of the moving wing ranges from 0.0 to 1.0. The physical phenomena over the wing dramatically vary with the reduced frequency. This study examines experimentally the effect of the reduced frequency at low Reynolds number. The NACA0012 airfoil performs sinusoidal pitching motion with respect to the quarter chord with the four reduced frequencies of 0.1, 0.2, 0.4 and 0.76 at the Reynolds number $2.3{\times}10^4$. Smoke-wire flow visualization, unsteady surface pressure measurement, and unsteady force calculation are conducted. At the reduced frequency of 0.1 and 0.2, various boundary layer events such as reverse flow, discrete vortices, separation and reattachment change the amplitude and the rotation direction of the unsteady force hysteresis. However, the boundary layer events abruptly disappear at the reduced frequency of 0.4 and 0.76. Especially at the reduced frequency of 0.76, the local variation of the unsteady force with respect to the angle of attack completely vanishes. These results lead us to the conclusion that the unsteady aerodynamic characteristics of the reduced frequency of 0.2 and 0.4 are clearly distinguishable and the unsteady aerodynamic characteristics below the reduced frequency of 0.2 are governed by the boundary layer events.

• Korea-Australia Rheology Journal
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• 제21권1호
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• pp.27-37
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• 2009

In this work, we numerically investigate the effect of viscoelasticity on 2D laminar vortex dynamics in flows past a single rotating cylinder for rotational rates $0{\leq}{\alpha}{\leq}5$ (the rotational rate ex is defined by the ratio of the circumferential rotating velocity to free stream velocity) at Re=100, in which the vortex shedding has been predicted to occur in literature for Newtonian fluids. The objective of the present research is to develop a promising technique to fully suppress the vortex shedding past a bluff body by rotating a cylinder and controlling fluid elasticity. The predicted vortex dynamics with the present method is consistent with the previous works for Newtonian flows past a rotating cylinder. We also verified our method by comparing our data with the literature in the case of viscoelastic flow past a non-rotating cylinder. For $0{\leq}{\alpha}{\leq}1.8$, the frequency of vortex shedding slightly decreases but the fluctuation of drag and lift coefficient significantly decreases with increasing fluid elasticity. We observe that the vortex shedding of viscoelastic flow disappears at lower ${\alpha}$ than the Newtonian case. At ${\alpha}$=5, the relationship between the frequency of vortex shedding and Weissenberg number (Wi) is predicted to be non-monotonic and have a minimum around Wi=0.25. The vortex shedding finally disappears over critical Wi number. The present results suggest that the vortex shedding in the flow around a rotating cylinder can be more effectively suppressed for viscoelastic fluids than Newtonian fluids.

• 해양환경안전학회지
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• 제22권7호
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• pp.892-899
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• 2016

본 연구에서는 세굴된 해저 파이프 주위 중력류의 유동 해석을 수행하였다. 결과 비교를 위해 세굴이 아닌 평평한 해저면 위에 틈새 거리를 두고 설치된 해저 파이프 문제를 함께 고려하였다. 여기서 세굴의 깊이와 틈새 거리는 동일하며, 평평한 해저면 위에 설치된 파이프 문제는 일반적으로 실제 세굴효과를 이상적으로 구현하기 위해 주로 고려된다. 중력류와 해저 파이프 상호작용에 대한 유동특성의 이해를 위해 농도 및 와도장, 압력장 그리고 양항력 계수 등, 다양한 물리량들을 비교 및 분석 하였다. 결과적으로 세굴과 평평한 해저면 위에 설치된 해저 파이프 주위 유동특성이 달라짐을 관찰하였다, 특히 세굴의 위 파이프의 경우 구조물 상부에서 발달된 음의 와만 하류로 나아가게 되지만 평탄면 위 파이프는 이열 와구조 형태를 가지는 것을 확인하였다. 따라서 중력류에 놓인 해저 파이프의 안전 설계를 위해서는 무엇보다 실제 세굴조건을 고려하는 것이 중요 할 것으로 판단된다.

• Wind and Structures
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• 제34권4호
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• pp.355-369
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• 2022

Section model test, as the most commonly used method to evaluate the aerostatic and aeroelastic performances of long-span bridges, may be carried out under different conditions of incoming wind speed, geometric scale and wind tunnel facilities, which may lead to potential Reynolds number (Re) effect, model scaling effect and wind tunnel scale effect, respectively. The Re effect and scale effect on aerostatic force coefficients and aeroelastic characteristics of streamlined bridge decks were investigated via 1:100 and 1:60 scale section model tests. The influence of auxiliary facilities was further investigated by comparative tests between a bare deck section and the deck section with auxiliary facilities. The force measurement results over a Re region from about 1×10⁵ to 4×10⁵ indicate that the drag coefficients of both deck sections show obvious Re effect, while the pitching moment coefficients have weak Re dependence. The lift coefficients of the smaller scale models have more significant Re effect. Comparative tests of different scale models under the same Re number indicate that the static force coefficients have obvious scale effect, which is even more prominent than the Re effect. Additionally, the scale effect induced by lower model length to wind tunnel height ratio may produce static force coefficients with smaller absolute values, which may be less conservative for structural design. The results with respect to flutter stability indicate that the aerodynamic-damping-related flutter derivatives 𝘈^*₂ and 𝐴^*₁𝐻^*₃ have opposite scale effect, which makes the overall scale effect on critical flutter wind speed greatly weakened. The most significant scale effect on critical flutter wind speed occurs at +3° wind angle of attack, which makes the small-scale section models give conservative predictions.