• Wind and Structures
• /
• 제22권2호
• /
• pp.253-272
• /
• 2016

The paper concerns with the method and results of wind tunnel investigations of the Strouhal number (St) of a stationary iced cable model of cable-supported bridges with respect to different angles of wind attack. The investigations were conducted in the Climatic Wind Tunnel Laboratory of the Czech Academy of Sciences in $Tel{\check{c}}$. The methodology leading to the experimental icing of the inclined cable model was prepared in a climatic section of the laboratory. The shape of the ice on the cable was registered by a photogrammetry method. A section of an iced cable model with a smaller scale was reproduced with a 3D printing procedure for subsequent aerodynamic investigations. The St values were determined within the range of the Reynolds number (Re) between $2.4{\cdot}10^4$ and $16.5{\cdot}10^4$, based on the dominant vortex shedding frequencies measured in the wake of the model. The model was oriented at three principal angles of wind attack for each of selected Re values. The flow regimes were distinguished for each model configuration. In order to recognize the tunnel blockage effect the St of a circular smooth cylinder was also tested. Good agreement with the reported values in the subcritical Re range of a circular cylinder was obtained. The knowledge of the flow regimes of the airflow around an iced cable and the associated St values could constitute a basis to formulate a mathematical description of the vortex-induced force acting on the iced cable of a cable-supported bridge and could allow predicting the cable response due to the vortex excitation phenomenon.

• Wind and Structures
• /
• 제3권3호
• /
• pp.209-220
• /
• 2000

The Strouhal number is an important nondimensional number which is explanatory of aerodynamic instability phenomena. It takes on the different characteristic constant value depending upon the cross-sectional shape of the body being enveloped by the flow. A number of investigations into this subject, especially on the drag test, surface pressure test and hot-wire test, have been carried out under the fixed state of the body in the past. However, almost no investigations concerning the determination of the St on wind-induced vibration of the body have been reported in the past even though the aerodynamic behavior of the body is very important because the construction of wind-sensitive structures is recently on the sharp increase. Based on a series of wind tunnel tests, this paper addresses a new method to determine the Strouhal number of rectangular cylinder in the uniform flow. The central idea of the proposed method is that the Strouhal number can be obtained directly by the aerodynamic behaviors of the body through wind-induced vibration test. The validity of proposed method is evaluated by comparing with the results obtained by previous studies in three B/Ds at attack angle $0^{\circ}$ and a square cylinder with various attack angles. The values and trends of the proposed Strouhal numbers are in good agreements with values of previous studies. And also, the Strouhal numbers of B/D=1.5 and 2.0 with various attack angles are obtained by the proposed method and verified by other method. This proposed method is as good as any other previous methods to obtain the Strouhal number.

• Wind and Structures
• /
• 제29권6호
• /
• pp.417-430
• /
• 2019

To study the wake influence of an upstream bridge on the wind-resistance performance of a downstream bridge, two adjacent long-span cable-stayed bridges are taken as examples. Based on wind tunnel tests, the static aerodynamic coefficients and the dynamic response of the downstream bridge are measured in the wake of the upstream one. Considering different horizontal and vertical distances, the flutter derivatives of the downstream bridge at different angles of attack are extracted by Computational Fluid Dynamics (CFD) simulations and discussed, and the change in critical flutter state is further studied. The results show that a train passing through the downstream bridge could significantly increase the lift coefficient of the bridge which has the same direction with the gravity of the train, leading to possible vertical deformation and vibration. In the wake of the upstream bridge, the change in lift coefficient of the downstream bridge is reduced, but the dynamic response seems to be strong. The effect of aerodynamic interference on flutter stability is related to the horizontal and vertical distances between the two adjacent bridges as well as the attack angle of incoming flow. At large angles of attack, the aerodynamic condition around the downstream girder which may drive the bridge to torsional flutter instability is weakened by the wake of the upstream bridge, and the critical flutter wind speed increases at this situation.

• 한국항공우주학회지
• /
• 제30권1호
• /
• pp.1-8
• /
• 2002

자유류 속도가 40 m/sec 이고 날개의 뿌리시위에 기준한 레이놀즈수가 1.76${\times}$10$^6$인 상태에서 옆미끄럼이 삼각 날개 와류에 미치는 영향을 실험적으로 연구하였다. 받음각 범위는 16$^{\circ}$에서부터 28$^{\circ}$까지 이었으며 옆미끄럼각은 0$^{\circ}$, -10$^{\circ}$, 그리고 -20$^{\circ}$이었다. 옆미끄럼각은 바람쪽과 바람 반대쪽 와류 모두의 강도를 감소시키고, 바람쪽 와류의 붕괴를 촉진시킴이 관찰되었다. 옆미끄럼각 -10$^{\circ}$에서 바람 반대쪽의 와류는 받음각이 증가함에 따라 그 강도가 증가하였다. 이와 같은 옆미끄럼 조건에서 날개 와류의 비대칭적인 발달과 붕괴는 삼각 날개의 롤링모멘트를 어느 특정한 높은 받음각에서 급격히 바뀌게 할 수 있으며, 이는 일종의 롤링 모멘트 불안정성으로 간주할 수 있다.

• 융합신호처리학회논문지
• /
• 제21권4호
• /
• pp.170-176
• /
• 2020

본 연구는 선박의 조종성능에 직접 영향을 미치는 방향타의 양력, 항력 및 모멘트를 전산유체역학을 이용하여 연구하였다. 힘과 모멘트에 영향을 미치는 전형적인 선박 방향타 중 하나는 바다에서 조종하는 동안 선수 타이다. 따라서 선박 선수타에 대한 힘과 모멘트를 연구하였다. IFS 선수 타 시리즈 중 균형 IFS 54 BR 15는 연구에 사용되었다. 난류 모델로는 표준 k-epsilon이 연구에 적용되었다. 선수 타의 유체 역학, 특히 양력, 항력 및 모멘트 계수는 서로 다른 공격 각도에 대해 계산되었다. 본 연구에 사용된 유동과 선수 타 사이의 받침각은 0도에서 5도 간격씩 35도까지 총 6개이다. 선박의 운동 성능에 미치는 영향에 대한 계산 결과는 이전 실험 연구 결과와 비교되었다.

• Structural Engineering and Mechanics
• /
• 제77권1호
• /
• pp.115-135
• /
• 2021

This paper focuses on examining the effects of span arrangements on displacement responses of plan-symmetric RC frame buildings designed using the direct displacement-based design (DDBD) method by employing non-linear analyses and the skew seismic attack. In order to show the desired performance of DDBD design approach, the force-based design approach is also used to examine the seismic performance of the selected structures. To realize this objective, 8-story buildings with different plans are selected. In addition, the dynamic behavior of the structures is evaluated by selecting 3, 7, and 12-story buildings. In order to perform non-linear analyses, OpenSees software is used for modeling buildings. Results of an experimental model are used to validate the analytical model implemented in OpenSees. The results of non-linear static and non-linear dynamic analyses indicate that changing span arrangements does not affect estimating the responses of structures designed using the DDBD approach, and the results are more or less the same. Next, in order to apply the earthquake in non-principle directions, DDBD structures, designed for one-way performance, are designed again for two-way performance. Time history analyses are performed under a set of artificial acceleration pairs, applied to structures at different angles. It is found that the mean maximum responses of earthquakes at all angles have very good agreement with the design-acceptable limits, while the response of buildings along the height direction has a relatively acceptable and uniform distribution. Meanwhile, changes in the span arrangements did not have a significant effect on displacement responses.

• 한국터널지하공간학회 논문집
• /
• 제16권6호
• /
• pp.573-584
• /
• 2014

본 연구에서는 로드헤더 커팅헤드 설계의 기본 사항인 절삭조건에 따른 커터작용력의 변화를 살펴보는 기초 연구를 진행하기 위하여 연암 및 보통암을 대상으로 하는 슬림 코니컬커터를 사용하여 받음각과 커터관입깊이, 커터간격의 조건에 따른 선형절삭시험을 수행하였다. 각 시험조건에서 커터작용력인 연직력, 절삭력, 구동력을 측정하였고 그 측정결과의 평균값을 사용하여 분석을 실시하였다. S/d비와 비에너지의 관계, 관입깊이와 비에너지의 관계, S/d비와 커터작용력의 관계로부터 받음각이 $50^{\circ}$, 커터간격이 12 mm, 커터관입깊이가 9 mm인 조건이 모르타르시험체에 대한 최적의 절삭조건임을 확인할 수 있었다. 특히 받음각이 $50^{\circ}$인 경우가 $45^{\circ}$인 경우에 비해 장비사양 설계를 위해 더 효과적임을 알 수 있었다.

• 대한조선학회논문집
• /
• 제48권2호
• /
• pp.128-133
• /
• 2011

In the present study, the flow fields in between the propeller and the semi-spade rudder are investigated by using PIV technique to find out the influences of both simulated hull wake and propeller wake on the incident flow to the rudder. The velocity fields are measured at the propeller rotation angle of $180^{\circ}$ and the rudder deflection angles of $0^{\circ}$. Flow fields measured at each rudder deflection angle are analyzed in terms of angle-of-attack against the rudder leading edge. The hull wake increases the angle-of-attack more than that in the uniform inflow condition, forming the angle-of-attack of about $20^{\circ}$ at 0.7R(R=propeller radius) position. The distribution of the angle-of-attack is strongly affected by the stagnation point around the leading edge and camber effect of the rudder. These effects provide asymmetric distribution of angle-of-attack with respect to the leading edge of the rudder.

• International Journal of Control, Automation, and Systems
• /
• 제2권4호
• /
• pp.494-500
• /
• 2004

The wing rock phenomenon is a high angle of attack aerodynamic motion manifested by limit cycle roll oscillations. Experimental studies reveal that direct control and manipulation of leading edge vortices, through the use of 'blowing' techniques is effective in the suppression of wing rock. This paper presents the design of a robust controller for the experimental implementation of one such 'blowing' technique - recessed angle spanwise blowing (RASB), to achieve wing rock suppression over a range of operating conditions. The robust controller employs Takagi - Sugeno fuzzy system, which is fine-tuned by experimental simulations. Performance of the controller is assessed by real-time wind tunnel experiments with an 80 degree swept back delta wing. Robustness is demonstrated by the suppression of wing rock at a range of angles of attack and free stream velocities. Numerical simulation results are used to further substantiate the experimental findings.

• International Journal of Naval Architecture and Ocean Engineering
• /
• 제11권1호
• /
• pp.225-232
• /
• 2019

In recent years, nonlinear dynamic models have been developed for flapping-type energy harvesting systems with a rigid wing, but not for those with a flexible wing. Thus, in this study, flexible wing designs of NACA0012 section are proposed and measurements of the forces of rigid cambered wings, which are used to estimate the performance of the designed wings, are conducted. Polar curves from the measured lift and drag coefficients show that JavaFoil estimation is much closer to the measured values than Eppler over the entire given range of angles of attack. As the camber of the rigid cambered wings is increased, both the lift and drag coefficients increase, in turn increasing the resultant forces. Moreover, the maximum resultant forces for all rigid cambered wings are achieved at the same angle of attack as the maximum lift coefficient, meaning that the lift coefficient is dominant in representations of the wing characteristics.