• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.06a
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• pp.1169-1173
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• 2000

최근에 미국에서는 실선에 대한 충격파 실험의 제약으로 인하여 수치시뮬레이션의 필요성이 더욱 야기되어 1996년도부터 수상함에 대한 실험대체용 수치계산의 가능성에 대한 연구가 시작되었다. 잠수함등과 같이 잠겨진 구조물에 대한 연구는 활발히 이루어졌으나 수상함에 대한 연구는 단순구조물을 대상으로 한 제한적 연구가 이루어져 왔다. 특히 본 연구에서는 아주 복잡한 수상함 구조물을 최대한 정확히 유한요소법으로 모델링하였다. 이러한 실선 충격연구는 실제 실선에 마운트되는 주요 장비의 안정성평가에 아주 중요한 자료를 제공하여주므로 시급한 과제이다. 하지만 수상함의 경우 유체-구조물 상호작용, 자유표면, cavitation등과 같은 해석상의 어려움과 복잡한 구조물의 모델링시 나타나는 현 단계에서의 계산상의 한계 등등 여러 가지 난제가 존재하고 있는 것도 사실이다. 본 논문에서는 수상함 내충격 수치해석의 현기술을 알아보고 수치계산의 발전방향을 제시보고자 한다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2003.05a
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• pp.168-173
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• 2003

This experimental study describes the propagation characteristics of the impulse noise emitted from the exit of a perforated pipe attached to the open end of a simple shock tube. The pressure amplitudes and directivities of the impulse wave propagating from the exit of perforated pipe with several different configurations are measured and analyzed fur the range of the incident shock wave Mach number between 1.02 and 1.2. In the experiments, the impulse waves are visualized by a Schlieren optical system for the purpose of investigating their propagation pattern. The results obtained show that for the near sound field the impulse noise strongly propagates toward to the pipe axis, but for the far sound field the impulse noise uniformly propagates toward to the all directions, indicating that the directivity pattern is almost same regardless of the pipe type. Moreover, it is shown that for the far sound field the perforated pipe has little performance to suppress the impulse noise.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.12 no.7
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• pp.510-519
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• 2002

The present study addresses a computational work of the weak shock wave propagating inside an automobile exhaust muffler. Several different types of the silencer systems are employed to investigate the magnitude of the shock wave during propagating through them. The Initial shock wave Mach number $M_s$ is varied between 1.01 and 1.30, and a normal shock wave is given at the inlet of the silencer systems. The second order total variation diminishing scheme Is employed to solve the two dimensional, compressible, unsteady Euler equations. The present computational results are compared with the previous experimental ones available. The present computations predict the experimental results with a quite good accuracy. Of the four silencer systems applied. the most desirable silencer system to reduce the peak pressure at the exalt of the exhaust pipe is discussed from the Point of view of the engineering design of the silencer systems.

• The Journal of the Acoustical Society of Korea
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• v.25 no.1
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• pp.43-48
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• 2006

When the vibration of a phantom induced by Extracorporeal Shock Wave Lithotripter (ESWL) was investigated. we found the fact that the Peak frequency in the Power spectrum shifts from high frequency to low frequency as the number of shots increases[2]. The fact was confirmed experimentally by detecting the peak frequency obtained from the vibrations of bronze models[3]. This Paper investigates the experimental results. For the Purpose. we carried out the computer simulation using the finite element method. It is found that the results from the experiments are computer by computer simulation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2009.10a
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• pp.282-287
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• 2009

본 논문에서는 사각판이 고정단을 경계조건으로 가진 상태에서 충격력을 받았을 때의 굽힘파 전파와 이에 의한 음향 방사가 특정 공간에서 이루는 음장을 유한 차분 시간 영역법을 이용하여 예측하였다. 이와 같은 시도는 향후 구조물에서의 진동과 음장 사이의 관계를 해석하는데 도움이 될 수 있을 것이다. 대상 시뮬레이션 모델은 한 쪽 끝이 철판으로 이루어진 직육면체의 공간이며 예측 결과를 실험값과 비교하였다. 예측 결과는 대체로 파형과 그 특성이 실험값과 잘 일치하였으나, 감쇠 알고리즘을 주파수 대역에 따라 달리 적용하지 못하였고, 사각 평판에서 충격력의 적용 범위가 모호하여, 파형의 크기에 차이가 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.8
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• pp.29-36
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• 2004

Supersonic inlet buzz can be defined as unstable subcritical operation associated with fluctuating internal pressures and a shock pattern oscillating about the inlet entrance. The flow pulsations could result in flameout in the combustor or even structural damage to the engine. An experimental study was conducted to investigate the phenomenon of supersonic inlet buzz on axisymmetric, external-compression inlet. An inlet model with a cowl lip diameter of 30mm was tested at a free stream Mach number of 2.0. Subcritical instability was investigated by considering the frequency of pressure pulsation and shock wave structure at the inlet entrance. The results obtained show that total pressure recovery ratios were varied from 0.42 to 0.78, and capture area ratio from 0.34 to 0.98. The frequency of the subcritical flow increased with decrease in capture area ratios. Frequency was measured at $224{\sim}240Hz$.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.11 no.7
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• pp.239-246
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• 2001

The present study addresses the open correction associated with the reflection and discharge phenomena of a weak shock wave from an open end of a duct. The open correction of the weak shock wave is investigated experimentally and by numerical computation. An experiment is made using a simple shock tube with an open end. and computaion is performed to simulate the experimental flow field using the unsteady, axisymmetric compressible. flow governing equations. The results obtained show the an open correction should be involved for shock wave discharge and reflection problems generated from the exit of the duct with an open baffle plate. With a baffle plate less than three times the duct diameter, it is found that the open end correction is a function of both the diameter of the baffle plate and normal shock wave magnitude However, for a baffle plate larger than three the duct diameter it is independent of the baffle plate diametre, The present computations predict the results of shock tube experiment with good accuracy. A new empirical equation for prediction of the open correction is found for the weak shock reflection and discharge phenomena occurring at the open of the duct with and without a baffle plate.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.11 no.9
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• pp.406-413
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• 2001

The current study depicts and experimental work of the impulsive wave discharged from the exit of several kinds of right-angle bend pipes, which are attached to the open end of a simple shock tube. The weak normal shock wave with Mach number from 1.02 to 1.20 is employed to obtain the impulsive wave propagating outside the exit of the pipe bends. The experimental data of the magnitude of the impulsive wave and its propagation directivity are analyzed to characterize the impulsive waves discharged from the right-angle bend pipes and compared with those from a straight pipe. The impulsive waves are visualized by a Schlieren optical system. A computation work using the two-dimensional, unsteady, compressible Euler equation is also carried out to represent the experimented impulsive waves. The results obtained show that a right-angle miter bend considerably reduces the magnitude of the impulsive wave and its directivity toward to the pipe axis, compared with the straight pipe. It is believed that the right angle miter bend pipe can play a role of passive control agianst the impulsive wave.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.11 no.5
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• pp.921-925
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• 2007

This paper investigates the information related to the radiated sounds during treatment using the extracorporeal shock wave lothotriptor(ESWL). First, we observe the vibration of the objects from the radiated sounds and extract the information about the change of the peak frequency from the relation between the vibration and the radiated sounds. Next, we observe the change of the peak frequency according to the position of the focus and demonstrate that it is more difficult to vibrate objects exactly at the focal point than above or below the focus of the ESWL device. Lastly, we analyze the relation between the cavitation and the radiated sounds and examine the benefiting condition for the object fragmentation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1996.10a
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• pp.443-449
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• 1996

헬리콥터, 팬, 프로펠러, 터이빈같이 회전익에서 유체역학적 소음이 발생하는 장치의 설계에 있어서는 공기 역학적 성능 분석과 함께 소음에 대한 해석이 절대적으로 필요하다. 근래에 들어와서 소음에 대한 관심이 급격히 증가하고 공항 주변에서의 국제적인 규약들은 낮은 소음 수준(low noise level)을 규정하고 있으며, 이에 따라서 소음을 감소시키려는 연구가 매우 활발히 진행되고 있는 실정이다. 더욱이 컴퓨터의 냉각 팬을 비롯한 공조기기 및 산업기기에 사용되는 회전기계에서 발생되는 소음의 저감은 보다 더 쾌적한 환경을 요구하는 사회적 요구에 부합하면서 공력소음의 연구 분야가 더 넓어지고 있다. 본 논문에서는 소음예측 방법중의 하나인 음향상사(acoustic analogy)를 주파수 영역 방법(frequency domain method)을 이용하여 헬리콥터 블레이드의 고속 충격소음(High Speed Impulsive Noise)을 해석한다. 고속 충격소음은 블레이드-와류 상호작용 소음과 더불어 헬리콥터의 지배적인 소음원으로서 깃끝 속도가 큰 전진 수평비행(forward level flight)또는 제자리 비행(hovering flight)시 발생하는 소음으로 블레이드의 깃끝 마하수(critical Mach number)보다 크거나 비슷할 경우 충격파의 교란에 의해서 일어나는 충격적인 소음을 말한다. 고속 충격소음은 고주파수 스펙트럼 성분과 큰 소음강도를 가지고 있기 때문에 날카로운 금속성의 소리를 내며 먼 거리까지 전파되는 특징을 가지고 있다.