• 전산구조공학
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• 제10권4호
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• pp.291-302
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• 1997

이 논문은 압축성 유체로 채워진 원통형 탱크의 고유진동 특성을 파악하기 위한 해석적 방법을 제시하고 있다. 탱크의 동적거동은 유한 Fourier 급수전개 방법으로 전개하였으며, 압축성 유체는 선형 포텐셜 이론으로 전개하였다. 해석방법의 타당성을 검증하기 위하여 물로 채워진 양단고정의 경계조건을 갖는 원통형 탱크의 고유진동수를 해석적 방법으로 구한 다음, 상용 유한요소해석 프로그램인 ANSYS 5.2를 이용하여 검증하였다. 그 결과, 유한요소해석결과와 이론적인 방법으로 구한 이론해가 잘 일치하고 있음을 확인하였다. 또한 유체의 밀도와 압축성이 탱크의 고유진동수에 미치는 영향을 정규화된 무차원 고유진동수를 통해서 평가하였다. 유체의 밀도는 탱크의 모든 진동 모드의 고유진동수에 영향을 주지만, 유체 압축성의 영향은 저차 원주방향 모드의 진동수에서 더 크게 나타나고 있음을 확인할 수 있었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2000년도 춘계 학술대회논문집
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• pp.113-119
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• 2000

Two-dimensional steady flow of two immiscible, compressible fluids are considered when the temperature of each layer is constant. Both upper and lower fluids are bounded by two horizontal rigid boundaries with symmetric obstruction of compact support at the tourer boundary. By using asymptotic method, we derive the forced K-dV equation governing interfacial wave. Various solutions and numerical results are presented.

• Structural Engineering and Mechanics
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• 제22권6호
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• pp.719-739
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• 2006

An analytical method for the free vibration of two circular plates coupled with an inviscid and compressible fluid is developed by the Rayleigh-Ritz method. The fluid is bounded by a rigid cylindrical vessel and two circular plates with an unequal thickness and diameter. It was found that the theoretical results could predict well the fluid-coupled natural frequencies with an excellent accuracy when compared with the finite element analysis results. As the fluid thickness increases or the plate thickness difference increases, an abrupt curve veering in the natural frequency loci of the neighboring modes and drastic changes in the corresponding mode shapes are observed. The mode localization frequently appears in the higher modes and in the wide gap between the plates because of a decrease in the fluid coupling owing to the fluid dispersion effect.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2000년도 춘계 학술대회논문집
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• pp.127-139
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• 2000

Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated using a two-dimensional turbulent compressible Navier-Stokes flow model. The spoiler moving relative to a stationary airfoil is treated by an overset grid bounded by a 'dynamic domain-dividing line' the concept of which is developed first..in this paper. The fluid-dynamic mechanism of the adverse lift due to the rapidly deploying spoiler is analyzed. Also the effect of spoiler deploying rate on the initial behavior of the aerodynamic response is expounded, which is of interest in view of active control technology and controller design for the spoiler. The results of present computation about the stationary as well as moving spoilers are relatively in good agreement with the existing experimental data.