• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2010년도 춘계학술대회 논문집
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• pp.340-341
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• 2010

A computational study to capture the flow around a floor mounted greenhouse shaped HAWT model was performed using the commercial software PowerFLOW 4.2b. The simulation kernel of this software is based on the numerical scheme known as the Lattice Boltzmann Method (LBM), combined with an RNG turbulence model. Simulations were performed at 60 and 140 km/h free stream air speeds. Selective results from these computational simulations are presented to show the capability of this numerical approach to predict the aerodynamics and aeroacoustics characteristics of the 3-D flow field around the HAWT model.

• 한국음향학회:학술대회논문집
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• 한국음향학회 1999년도 학술발표대회 논문집 제18권 2호
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• pp.433-438
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• 1999

본 논문은 기계장치에서 발생하는 소음 중 불필요한 소음만을 제거하고 실제로 필요한 소음(경고음 작동음 등)의 정보를 가진 소리는 제거하지 않는 소음 제어 방법을 Active Noise Control(ANC)를 이용하여 구현하였다. 소음원으로는 축류팬(Akial Fan)을 사용하였으며 여기서 발생하는 BPF를 효과적으로 제어할 수 있는 Feedback Active Noise Control 방식을 사용하였으며 적응 알고리즘으로 Filtered-X LMS 알고리즘을 사용하였다. 실험은 두 가지 Case(덕트 내 전파 소음, 외부 자유 음장 방사 소음)로 실행되었다. 제거하고자하는 대상은 BPF 소음이며 이 이외의 주파수에는 영향을 주지 않게 하기 위하여 대역필터를 이용하였다. 또한 실제 인간이 느끼는 소음 감소 효과를 알아보기 위해 Loudness로 제어 전후의 결과를 비교하였다. 실험 결과 BPF만 감소시키고 BPF이외의 주파수에는 영향을 주지 않음을 알 수 있었으며 6.7dB의 Loudness level의 감소 효과를 얻어, 제어하고자 하는 주파수만을 제어하였으며 음압뿐 아니라 인간이 느끼는 소음도에서도 효과적으로 감소할 수 있음을 확인할 수 있었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 학술대회
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• pp.297-301
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• 2008

The flight vehicles have cavities such as wheel wells and bomb bays. The flow around a cavity is characterized as unsteady flow because of the formation and dissipation of vortices due to the interaction between the freestream shear layer and cavity internal flow, the generation of shock and expansion waves. Resonance phenomena can damage the structures around the cavity and negatively affect aerodynamic performance and stability. The flow field is observed to oscillate in the "shear layer mode" with low aspect ratio. In the present study, numerical analysis was performed for cavity flows by the unsteady compressible three dimensional Reynolds-Averaged Navier-Stokes (RANS) equations with Wilcox's $\kappa$-$\omega$ turbulence model. The flow field is observed to oscillate in the shear layer mode" with large aspect ratio. Based on the SPL(Sound Pressure Level) analysis of the pressure variation at the cavity trailing edge, the dominant frequency was analyzed and compared with the results of Rossiter's formul. The aero-acoustic wave analyzed with CPD(Correlation of Pressure Distribution).

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년 추계학술대회논문집
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• pp.297-301
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• 2008

The flight vehicles have cavities such as wheel wells and bomb bays. The flow around a cavity is characterized as unsteady flow because of the formation and dissipation of vortices due to the interaction between the freestream shear layer and cavity internal flow, the generation of shock and expansion waves. Resonance phenomena can damage the structures around the cavity and negatively affect aerodynamic performance and stability. The flow field is observed to oscillate in the "shear layer mode" with low aspect ratio. In the present study, numerical analysis was performed for cavity flows by the unsteady compressible three dimensional Reynolds-Averaged Navier-Stokes (RANS) equations with Wilcox's ${\kappa}-{\varepsilon}$ turbulence model. The flow field is observed to oscillate in the "shear layer mode" with large aspect ratio. Based on the SPL(Sound Pressure Level) analysis of the pressure variation at the cavity trailing edge, the dominant frequency was analyzed and compared with the results of Rossiter's formul. The aero-acoustic wave analyzed with CPD(Correlation of Pressure Distribution).

• International Journal of Aeronautical and Space Sciences
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• 제11권4호
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• pp.319-325
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• 2010

For decades, researchers have rigorously studied the characteristics of flow traveling around blunt objects in order to gain greater understanding of the flow around aircraft, vehicles or vessels. Many different types of flow exist, such as boundary layer flow, flow separation, laminar and turbulent flow, vortex and vortex shedding; such types are especially observed around circular cylinders. Vortex shedding around a circular cylinder exhibits a two-dimensional flow structure possessing a Reynolds number within the range of 47 and 180. As the Reynolds number increases, the Karman vortex changes into a three-dimensional flow structure. In this paper, a numerical analysis was performed examining the flow and aero-acoustic field characteristics around a circular cylinder using an optimized high-order compact scheme, which is a high order scheme. The analysis was conducted with a Reynolds number ranging between 300 and 1,000, which belongs to B-mode flow around a circular cylinder. For a B-mode Reynolds number, a proper spanwise length is analyzed in order to obtain the characteristics of three-dimensional flow. The numerical results of the Strouhal number as well as the lift and drag coefficients according to Reynolds numbers are coincident with the other experimental results. Basic research has been conducted studying the effects an unstable three-dimensional wake flow on an aero-acoustic field.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2008년도 추계학술대회논문집
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• pp.545-560
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• 2008

O Source import ㅁDirect import form Nastran, ANSYS ㅁDirect import of all the RPM from the files containing the structural results O Solver ㅁDirect computation of all RPM (multiple load case): one matrix resolution with multiple RHS ㅁEfficient solvers (MUMPS, SPARSE, Iterative) ㅁFrequency parallelisms available for very large problems O In practice ㅁSmall problems run on a desktop ㅁLarge problems can exceed 3kHz on a car engine O Easy to mesh ㅁ3D model created in a few minutes thanks to the unequal meshes. O And all Actran standard features

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2000년도 춘계 학술대회논문집
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• pp.1-13
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• 2000

This paper presents a review of the methodology, problems and progress in computational aeroacoustics(CAA). The nature, characteristics, and objectives of aeroacoustics problems are quite different from the commonly encountered CFD problems. In this paper, computational methods that are designed especially for CAA applications are introduced. The potential offered by CAA, the numerical issues which need to be given careful attention, and some of the recent progress in solving aeroacoustic problem are discussed

• 한국전산유체공학회지
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• 제15권2호
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• pp.7-13
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• 2010

Flight vehicles such as wheel wells and bomb bays have many cavities. The flow around a cavity is characterized as an unsteady flow because of the formation and dissipation of vortices brought by the interaction between the free stream shear layer and the internal flow of the cavity. The resonance phenomena can damage the structures around the cavity and negatively affect the aerodynamic performance and stability of the vehicle. In this study, a numerical analysis was performed for the cavity flows using the unsteady compressible three-dimensional Reynolds-Averaged Navier-Stokes (RANS) equation with Wilcox's turbulence model. The Message Passing Interface (MPI) parallelized code was used for the calculations by PC-cluster. The cavity has aspect ratios (L/D) of 5.5 ~ 7.5 with width ratios (W/D) of 2 ~ 4. The Mach and Reynolds numbers are 0.4 ~ 0.6 and $1.6{\times}10^6$, respectively. The occurrence of oscillation is observed in the "shear layer and transient mode" with a feedback mechanism. Based on the Sound Pressure Level (SPL) analysis of the pressure variation at the cavity trailing edge, the dominant frequencies are analyzed and compared with the results of Rossiter's formula. The dominant frequencies are very similar to the result of Rossiter's formula and other experimental datum in the low aspect ratio cavity (L/D = ~4.5). In the high aspect ratio cavity, however, there are other low dominant frequencies of the leading edge shear layer with the dominant frequencies of the feedback mechanism.

• 한국음향학회지
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• 제33권1호
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• pp.40-47
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• 2014

원심팬 날개 깃에서 발생한 와류와 원심팬 볼루트 사이의 상호작용은 원심팬의 주요한 소음원으로 알려져 있다. 본 연구에서는 저소음 설계의 기초 자료로 활용하기 위하여 원심팬의 주요한 소음원 영역으로 고려되는 원심팬 볼루트 영역을 세분화하여 볼루트 영역내의 상대적 기여도를 분석한다. 주요한 소음원으로부터 방사되는 소음을 예측하기 위해 내부 음장용 복합 전산공력음향학(CAA, Computational Aero-Acoustics) 방법을 사용한다. 이 방법은 전산유체역학(CFD, Computational Fluid Dynamics)과 음향상사법(Acoustic Analogy), 그리고 경계요소법(BEM, Boundary Element Method)을 사용하여 원심팬 내부 유동장으로부터 방사한 소음을 원심팬 외부 음향장에서 예측하는 방법이다. 복합 CAA 방법을 이용한 원심팬 볼루트 영역내의 소음원의 상대적 기여도 분석은 컷-오프영역으로부터 출구영역보다 컷-오프영역으로부터 원심팬 스크롤영역이 전체 소음에 대한 기여도가 높고, 날개 깃의 쉬라우드 영역보다 허브 영역이 전체 소음에 대한 기여도가 높다는 것을 보여준다. 이러한 결과는 향후 저소음 원심팬 개발을 위한 유용한 자료로 활용될 것이다.

• 한국전산유체공학회지
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• 제20권2호
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• pp.67-72
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• 2015

In this paper, study of high speed train pantograph arm shape and panhead cross-section for aerodynamic drag and noise reduction is performed. In previous research, it is known that knee of pantograph arm and panhead of pantogpraph are main sources of noise from high speed train pantograph. By numerical simulation using full scale pantograph model, pantograph arm and panhead optimization are performed. As a result, drag and noise are reduced at both studies about high speed pantograph.