• Advances in aircraft and spacecraft science
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• 제1권1호
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• pp.27-41
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• 2014

An active flow control technique based on "smart-tabs" is proposed to delay flow separation on a circular cylinder. The actuators are retractable and orientable multilayer piezoelectric tabs which protrude perpendicularly from the model surface. They are mounted along the spanwise direction with constant spacing. The effectiveness of the control was tested in pre-critical and in post-critical regime by evaluating the effects of several control parameters of the tabs like frequency, amplitude, height, angular position and plate incidence with respect to the local flow. Measurements of the mean static pressure distribution around the cylinder were used to estimate the pressure drag coefficient. The maximum drag reduction achieved in the pre-critical regime was of the order of 30%, whereas in the post-critical regime was about 10%, 3% of which due to active forcing. Furthermore, pressure fluctuation measurements were performed and spectral analysis indicated an almost complete suppression of the vortex shedding in active forcing conditions.

• Ocean Systems Engineering
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• 제3권3호
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• pp.167-180
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• 2013

Hydrodynamic characteristics of a bluff cylinder oscillating along transverse direction in steady flow were experimentally investigated at Reynolds number of $2{\times}10^5$. The effects of non-dimensional frequency, oscillating amplitude and Reynolds number on drag force, lift force and phase angle are studied. Vortex shedding mechanics is applied to explain the experimental results. The results show that explicit similarities exist for hydrodynamic characteristics of an oscillating cylinder in high and low Reynolds number within subcritical regime. Consequently, it is reasonable to utilize the test data at low Reynolds number to predict vortex induced vibration of risers in real sea state when the Reynolds numbers are in the same regime.

• 조명전기설비학회논문지
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• 제27권12호
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• pp.63-73
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• 2013

The parameters of electromechanical modes offer considerable insight into the dynamic stability properties of a power system. This paper presents a results of a LFO(low-frequency oscillation) based on the time-synchronized signals measured by synchrophasor in the rolling blackout. Spectral analysis was performed, and critical parameters were estimated using the data acquired from synchrophasors installed in the KEPCO system. As significant modes, a 0.68 Hz oscillation mode that occurred prior to the forced load shedding in the rolling blackout was estimated. Such an oscillation mode can cause an uncontrollable blackout. Therefore, the system should be operated so that significant oscillation modes are not activated. This results can serve as a reference in the future for reliable system operation in the event of a similar blackout.

• Wind and Structures
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• 제5권6호
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• pp.479-492
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• 2002

A finite element aerodynamic model that can be used to analyse flutter instability of long span bridges in the time domain is presented. This approach adopts a simplified quasi-steady formulation of the wind forces neglecting the vortex shedding effects. The governing equations used are effective only for reduced velocities $V^*$ sufficiently great: this is generally acceptable for long-span suspension bridges and, then, the dependence of the wind forces expressions of the flutter derivatives can be neglected. The procedure describes the mechanical response in an accurate way, taking into account the non-linear geometry effects (large displacements and large strains) and considering also the compressed locked coil strands instability. The time-dependence of the inertia force due to fluid structure interaction is not considered. The numerical examples are performed on the three-dimensional finite element model of the Great Belt East Bridge (DK). A mode frequency analysis is carried out to validate the model and the results show good agreement with the experimental measurements of the full bridge aeroelastic model in the wind tunnel tests. Significant parameters affecting bridge response are introduced and accurately investigated.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.522-525
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• 2009

하이브리드 로켓의 연소 과정에서 DC-shift 현상을 관찰할 수 있다. 이와 같은 현상은 갑작스런 구조적 문제를 일으키거나 추력의 상승 또는 감소를 가져와 추력 성능의 저하를 유발한다. DC-shift 현상에 대한 이해를 통해 하이브리드 로켓의 연소 안정의 조건을 알 수 있다. 이 논문에서는 예-혼합실과 후-연소실을 장착하고 산화제 공급 유동 조건을 달리 함으로서 Negative DC-shift 현상을 유도하고 다양한 산화제 공급 유동 조건에 따른 Negative DC-shift 현상의 발생 조건과 특징에 대하여 알아보았다. Negative DC-shift 현상에 대한 실험적 연구를 통하여 Negative DC-shift 현상의 발생 원인과 현상의 특징에 대해 정의하였다.

• Journal of Advanced Marine Engineering and Technology
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• 제32권6호
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• pp.901-907
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• 2008

The measurements of velocity vectors are made in the wake(X/d=8) of a circular cylinder with arc grooves. The experiments are conducted by changing the groove number. groove depth, Reynolds number(Re) and the angle of the first formed groove. We know that the optimum groove angle is 70 degree and the wake velocity profiles are improved at a few conditions. According to vortex shedding frequency distributions. the key solutions to vary the flow field behind the circular cylinder are 70 degree groove angle and more deeper grooves than 0.2mm depth.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2006년도 추계 학술대회논문집
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• pp.93-96
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• 2006

The heat transfer enhancement by pulsatile flow in the plate heat exchanger has been investigated numerically in the present study. The numerical study was performed in the range of the mass flux from 0.04 to 0.12 kg/s. The results showed that the pulsatile flow produces resonating vortex shedding at the groove sharp edges and a strong transient vortex rotation within the grooved channels. As a result, the mixing between the trapped volume in the grooved cavity and the main stream was enhanced. Good agreements between the predictions and measured data are obtained in steady flow. And the heat transfer of pulsatile flow is about 2.4 times than steady flow when frequency is 10 Hz and the mass flux of cold side is 0.04 kg/s.

• 한국전산유체공학회지
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• 제15권4호
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• pp.60-66
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• 2010

Unsteady Reynolds Averaged Navier-Stokes(URANS) and Large Eddy Simulation(LES) simulation of an axial flow fan are calculated upon same conditions and computational grids in order to study aeroacoustic noise of an axial flow fan numerically. Results of computed performance and predicted noise are compared with those of measurement. Both performances show accurate results with a significant difference of less than 5%. However, noise of LES result is more close to measured noise qualitatively than URANS. Levels of tonal noises of both LES and URANS are quite similar with those of measured at BPF(Blade Passing Frequency) in sound spectrum. However, as leading edge separation and tip vortex shedding phenomena of LES are showed more clearly than those of URANS, sound level of broadband noise of LES corresponds better than that of URANS, especially.

• Journal of Advanced Marine Engineering and Technology
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• 제16권4호
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• pp.39-49
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• 1992

The coherent wake structures behind a spinning cylinder placed in a uniform flow were experimentally investigated by means of phase averaging technique. With a fixed cylinder Reynolds number (Re=6,600), the conditionally sampled velocity vectors were obtained at a section of 3.0 and 10 diameters behind the cylinder for the range of spin parameter S(the ratio of the peripheral velocity to that of the uniform flow) 0 to 2. Spectral analysis and vorticity contours of the velocity data show that up to S=1.2, a Karman vortex street exists within the wake, however, the coherent structures become obscure and their vorticity strength decreases as S increase. Beyond S=1.2, a distinct vortex shedding frequency no longer exists, furthermore coherent structures disappear when S is over 1.6.

• Journal of Advanced Marine Engineering and Technology
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• 제24권3호
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• pp.58-69
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• 2000

An experimental study was conducted to investigate the influence of the spinning control cylinders which was set on the surface of a fixed circular cylinder in uniform flow, $Re=1.24\times10^4$. The measurements of velocity vectors and pressure distributions are carried out in various spin parameters and angles of spinning control cylinder. The results show that velocity profiles and pressure distributions are different with angles of control cylinder and spin parameters. When the control cylinder angle is $100^{\circ}$, there is more effect in increasing the velocity and the pressure distribution than other cases. In this case, the vortex shedding frequency was increased as increasing spin parameter.