• 국제초고층학회논문집
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• 제11권4호
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• pp.315-320
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• 2022

With the rapid development of urbanization the problems of pedestrian-level wind comfort and natural ventilation of tall buildings are becoming increasingly prominent. The velocity at the pedestrian level ($\overline{MVR}$) and variation of wind pressure coefficients $\overline{{\Delta}C_p}$ between windward and leeward surfaces of tall buildings were investigated systematically through numerical simulations. The examined parameters included building density ρ, height ratio of building α_H, width ratio of building α_B, and wind direction θ. The linear and quadratic regression analyses of $\overline{MVR}$ and $\overline{{\Delta}C_p}$ were conducted. The quadratic regression had better performance in predicting $\overline{MVR}$ and $\overline{{\Delta}C_p}$ than the linear regression. $\overline{MVR}$ and $\overline{{\Delta}C_p}$ were optimized by the NSGA-II algorithm. The LINMAP and TOPSIS decision-making methods demonstrated better capability than the Shannon's entropy approach. The final optimal design parameters of buildings were ρ = 20%, α_H = 4.5, and α_B = 1, and the wind direction was θ = 10°. The proposed method could be used for the optimization of pedestrian-level wind comfort and natural ventilation in a residential area.

• Wind and Structures
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• 제36권3호
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• pp.175-200
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• 2023

The large eddy simulation (LES) of the flow around a circular cylinder is not only affected by the sub-grid scale (SGS) model but also by the grid resolution of the computational domain. To study the influence of different grids on the LES results, the LES simulations of the flow around a circular cylinder with different grids at Reynolds number (Re) = 3900 was performed. A circular computational domain with different radial growth rates and circumferential and spanwise grid numbers was adopted for the simulations. Meanwhile, the aerodynamic forces, wind pressure coefficients, mean and instantaneous flow fields, and the effect of grid resolution on them were comprehensively analyzed. The results indicate that the lift coefficient, wind pressure coefficient, and recirculation length are significantly affected by the radial growth rate of the grid and the circumferential grid number. The spanwise grid number has a significant influence on the three-dimensionality of the flow and plays an important role in velocity fluctuations in the wake region. Nevertheless, the aerodynamic coefficients and recirculation length are not sufficiently sensitive to the grid number in the spanwise direction. By comparing the results, it can be concluded that suitable and reliable LES results can be obtained when the radial growth rate is 1.03 or 1.05, the circumferential grid number is 160, 200, or 240, and the spanwise grid number is 64. A radial growth rate 1.05, circumferential grid number 160, and spanwise grid number 64 are recommended to reduce the grid amount and further improve the efficiency.

• 한국수산과학회지
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• 제30권2호
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• pp.188-202
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• 1997

본 연구에서는 한국 동해에서의 바람장의 공간적인 분포특성을 정량적으로 파악하기 위하여 해면기압과 해상풍 자료에 EOF 분석방법을 적용하여 모드별로 고유함수의 공간적인 분포특성과 시간계수를 계산하였고 시간계수의 스펙트럼을 구하여 바람장의 공간 및 시간변동성 및 주기적인 특성을 파악하였다. 평균기압의 분포는 서고동저형의 등압선 배치를 나타내며, 기압의 최대 표준 편차는 블라디보스톡 부근에 위치하고 일본연안으로 갈수록 최저 표준편차를 갖는다. 블라디보스톡 부근은 $6.5^{\circ}C$의 해수면 온도의 최대 표준편차를 갖는 지역이기도 하다. 동서성분 해상풍의 제1모드는 분산의 $47.3\%$ 제2모드는 $30\%$를 반영하며 제1모드는 블라디보스톡 해역에서 최대 변화를 보이며 1년 및 6개월의 주기를 갖는다. 특히 제2모드에서 6개월의 주기가 탁월하다. 해상풍의 남북성분의 연평균 분포는 동해전역에서 북풍계열의 바람이 탁월하며, 특히 블라디보스톡 부근에서 최대 2.2m/s 이상의 북풍이 존재하고 3.8m/s의 표준편차 최대치가 존재하며 시간변동이 크다. 해수면 수온의 공간분포 역시 블라디보스톡 해역에서 최대치가 나타난다. 해상풍과 해면 기압의 결합 직교함수의 모드별 특성은 개별 직교함수에 비해 동서성분 해상풍의 제1모드의 기여도가 증가 하였으며, 제2모드의 기여도는 감소하는 양상을 띤다. 이로 인해 동서성분 해상풍과 해면기압의 결합 직교함수 (WU-PR)의 주기성은 해면 기압의 영향으로 제1모드에서는 1년 및 6개월의 주기가 탁월하며, 제2모드에서는 3개월의 계절변화로 해상풍의 개별 직교함수의 주기와 다르게 나타난다. 해수면 온도의 직교함수까지 포함한 3개의 결합 직교함수의 EOF분석에서는 제2모드에서 해상풍의 공간분포는 해수면 온도에 좌우되는 양상을 보인다. 스펙트럼 분석결과는 제1모드에서 1년 주기가 탁월하며 제2모드는 3개월 및 4개월의 계절변화가 나타난다.

• Wind and Structures
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• 제17권1호
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• pp.1-19
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• 2013

A multiscale finite element method is applied to the Spalart-Allmaras turbulence model based detached-eddy simulation (DES). The multiscale arises from a decomposition of the scalar field into coarse (resolved) and fine (unresolved) scales. It corrects the lack of stability of the standard Galerkin formulation by modeling the scales that cannot be resolved by a given spatial discretization. The stabilization terms appear naturally and the resulting formulation provides effective stabilization in turbulent computations, where reaction-dominated effects strongly influence near-wall predictions. The multiscale DES is applied in the context of high-Reynolds flow over the Commonwealth Advisory Aeronautical Council (CAARC) standard tall building model, for both uniform and turbulent inflows. Time-averaged pressure coefficients on the exterior walls are compared with experiments and it is demonstrated that DES is able to resolve the turbulent features of the flow and accurately predict the surface pressure distributions under atmospheric boundary layer flows.

• Journal of Advanced Marine Engineering and Technology
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• 제25권5호
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• pp.1091-1097
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA 00XX and 44XX airfoils. The six flaps which have 0.5% chord height difference were selected . A Navier-Stokes code, FLUENT, was used to calculate the flow field of the airfoil. The code was first tested as a benchmark by modelling flow around a NACA 4412 airfoil. Predictions of local pressure coefficients are found to be in good agreement with the result of the experimental results. For every NACA 00XX and 44XX airfoil, flap heights ranging from 0.0% to 2.5% chord were changed by 0.5% chord interval and their effects were also studied. Representative results from each case are presented graphically and discussed. It is conclued that this initial approach gives an idea for the future development of the wind turbine optimum design.

• 한국전산유체공학회지
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• 제10권2호
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• pp.60-68
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• 2005

For study on the unsteady wall interference effect, flows around a forced oscillating airfoil in closed test-section wind tunnels have been numerically investigated by solving compressible Navier-Stokes equations. The numerical scheme is based on a node-based finite-volume method with the Roe's flux-difference splitting and an implicit time-integration method coupled with dual time-step sub-iteration. The Spalart-Allmaras one-equation model is employed for the turbulence effect. The computed results of the oscillating airfoil having a thin wake showed that the lift curve slope is increased and the magnitude of hysteresis loop is reduced by the interference effects. Since the vortex around the airfoil is generated and convected downstream faster than the free-air condition, the phase of lift, drag and pitching moment coefficients was shifted. The pressure on the test section wall shows harmonic terms having the oscillating frequency contained in the wail effect.

• 한국마린엔지니어링학회:학술대회논문집
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• 한국마린엔지니어링학회 2001년도 춘계학술대회 논문집
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• pp.58-62
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap. height using NACA 0006, 0009, 0012, 0015, 0018, 0021 and 0024 airfoils. The six flaps which have 0.5% chord height difference were used. A Navier-Stokes code, FLUENT, was used to calculate the flow field of the airfoil. The code was first tested as a benchmark by modelling flow around a NACA 4412 airfoil. Predictions of local pressure coefficients are found to be in good agreement with the result of the experimental result. For every NACA 00XX airfoil, flap heights ranging from 0.0% to 2.5% chord were changed by 0.5% chord interval and their effects were also studied. Representative results from each case are presented graphically and discussed. It is concluded that this initial approach gives a promise for the future development of wind turbine optimum design.

• 한국항공우주학회지
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• 제36권4호
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• pp.337-345
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• 2008

연구에서는 NACA4412익형으로 이루어진 주날개에 NACA0012플랩이 장착된 아음속 벽면효과 모형(SWIM)의 날개 표면 3차원 압력 분포를 압력감응페인트를 이용하여 시험적으로 연구하였다. 한국항공우주연구원의 아음속 풍동에서 레이놀즈수 3.1x105의 조건에서 시험 모형의 받음각 변화에 따른 날개 윗면 및 아랫면의 압력 분포를 측정하였다. 그 결과 받음각이 증가함에 따라 날개 윗면에서의 최저 압력 지점이 뿌리에서 끝단으로 이동을 하는 것을 관찰하였고, 날개 끝단의 뒷전에서도 끝단 와류를 일으키는 압력이 매우 낮은 지점도 관찰되었다. 그러나 실속각 이후인 받음각 15도의 경우 끝단 뒷전에서는 압력이 낮은 지점이 계속 관찰되었으나 그 이외의 부분은 스팬 방향 압력 분포가 편평하였다. 압력감응페인트와 더불어 압력공을 사용하여 날개의 코드 방향 2차원 압력분포도 측정 하여 비교하였고 두 시험에서 측정된 각 압력계수들의 차이의 평균은 약 0.077임을 확인하였다.

• Wind and Structures
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• 제34권5호
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• pp.421-435
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• 2022

To investigate the non-Gaussian properties of fluctuating wind pressures and the error margin of extreme wind loads on a long-span curved roof with matching and mismatching ratios of turbulence integral scales to depth (L_u^x/D), a series of synchronized pressure tests on the rigid model of the complex curved roof were conducted. The regions of Gaussian distribution and non-Gaussian distribution were identified by two criteria, which were based on the cumulative probabilities of higher-order statistical moments (skewness and kurtosis coefficients, S_k and K_u) and spatial correlation of fluctuating wind pressures, respectively. Then the characteristics of fluctuating wind-loads in the non-Gaussian region were analyzed in detail in order to understand the effects of turbulence integral-scale. Results showed that the fluctuating pressures with obvious negative-skewness appear in the area near the leading edge, which is categorized as the non-Gaussian region by both two identification criteria. Comparing with those in the wind field with matching L_u^x/D, the range of non-Gaussian region almost unchanged with a smaller L_u^x/D, while the non-Gaussian features become more evident, leading to higher values of S_k, Ku and peak factor. On contrary, the values of fluctuating pressures become lower in the wind field with a smaller L_u^x/D, eventually resulting in underestimation of extreme wind loads. Hence, the matching relationship of turbulence integral scale to depth should be carefully considered as estimating the extreme wind loads of long-span roof by wind tunnel tests.

• 한국항공우주학회지
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• 제48권2호
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• pp.119-125
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• 2020

본 논문에서는 국방과학연구소에서 신규 건설한 천음속풍동을 소개하고 성능에 대하여 기술하였다. 천음속풍동은 인젝터구동(Injection Driven), 폐회로(Closed Circuit) 방식의 풍동으로 시험부 크기가 가로, 세로 각각 1.5m이다. 마하수는 0.3에서 1.2까지 연속적으로 변화가능하며, 노즐을 교체하여 마하수 1.4 실험이 가능하다. 풍동의 전압력(Total Pressure)을 100kPa에서 550kPa까지 변화시킬 수 있으며, 그에 따라 레이놀즈수(Reynolds Number)를 크게 변화시켜 실험을 수행할 수 있다. 풍동의 성능을 검증하기 위하여 AGARD-B 표준모형을 이용하여 6분력 공력계수 측정 실험을 수행하였으며, 그 결과를 국과연 삼중음속풍동 및 세계 여러 풍동의 실험결과와 비교 분석하였다.