• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.31-36
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• 2006

In this study, nonlinear static aeroelastic analysis system for a high-aspect-ratio wing are developed using the transonic small disturbance (TSD) and large deflection beam theory and validated. For the coupling between fluid and structure, the transformation of displacement from the structural mesh to aerodynamic one is performed by the shape function of the beam finite element and the inverse transformation of force by work equivalent load concept. Also, for the static aeroelastic analysis of the wing the use of TSD aerodynamics are justified. The validation of the system includes one of the efficient transformation methods of force and displacement.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.581-585
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• 2007

Sonic arc airfoil derived from the TSD theory is modified to new airfoil shape and its aerodynamic performance in transonic flow is investigated. The numerical simulation using Euler equations for the modified sonic arc airfoil is performed. The numerical results are compared with the aerodynamic performance of NACA0012 airfoil, of supercritical airfoil, and of NACA64A210 airfoil. In the same free stream Mach number of transonic flow, the pressure drag of the modified sonic arc airfoil is smaller than that of NACA0012 airfoil and the lift-drag ratio of the modified sonic arc airfoil is much larger than that of NACA0012 airfoil. In the comparison of the drag-divergence Mach number of transonic flow, the drag-divergence Mach number of the modified sonic arc airfoil is larger than that of NACA64A210 airfoil but is smaller than that of supercritical airfoil.

• Journal of KSNVE
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• v.3 no.4
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• pp.293-299
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• 1993

최근 토목, 건축재료 및 시공기술의 발전과 더불어 컴퓨터를 이용한 해석 기법의 개발, 경제규모의 확대, 주변환경과의 조화 및 미적감가의 끊임없는 추구는 구조물의 장대화, 연성화, 다양화는 물론 구조감쇠율의 감소 등을 가져옴으로서 바람에 의한 동적 거동의 영향이 증대되어 이에 대한 검토의 중요성이 크게 부각되기 시작하였다. 특히, 최근들어 활발히 계획, 공사중인 여러 현수교, 사장교 구조물 중 시공단계로서의 독립 tower, 발전소의 장대 굴뚝, 고층건물, 전망 tower, 공항 관제 탑 등이 좋은 예이다. 따라서 이들 구조물의 설계과정에서 제안된 여러형태의 진동 제어 방법중 수동 감쇠장치에 대하여 소개하기로 한다. 감쇠장치는 직접 외부에 부착 하는 강제 감쇠장치와 소량의 질량, 스프링과 감쇠장치들을 조합하여 부착하는 수동 감쇠장치가 있다. 수동감쇠장치는 소규모로서 유지보수가 거의 필요 없으며 외관의 변화가 거의 없고 저렴하다는 장점이 있다. 여러종류의 수동감쇠장치, 즉 TMD, IMD 그리고 TSD에 대한 개략적인 이론과 그 사용예에 대하여 설명하였다. 실험적 검증 및 실측결과 각 장치가 바람에 의해 야기되는 진동현상을 억제하는데 매우 유효한 것으로 판정되었고 또한 크기가 소규모일 뿐 아니라 유지보수가 거의 없으며 비용도 저렴하여 국내 건설 또는 건설예정인 유사구조물에도 많은 적용이 예상된다.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.12 no.11
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• pp.864-872
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• 2002

In this study, the effect of planform curvature on the stability of coupled flow/structure vibration is examined in transonic and supersonic flow regions. The aeroelastic analysis for the frequency and time domain is performed to obtain the flutter solution. The doublet lattice method(DLM) in subsonic flow is used to calculate unsteady aerodynamics in the frequency domain. For all speed range, the time domain nonlinear unsteady transonic small disturbance code has been incorporated into the coupled-time integration aeroelastic analysis (CTIA). Two curved wings with experimental data have been considered in this paper MSC/NASTRAN is used for natural free vibration analyses of wing models. Predicted flutter dynamic pressures and frequencies are compared with experimental data in subsonic and transonic flow regions.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.6
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• pp.23-29
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• 2003

Transonic two-phase flow of Saturated humid air, in which relative humidity is 100%, with various condensation processes around thin airfoils is investigated. The study uses an extended transonic small-disturbance(TSD) model of Rusak and Lee [11, 12] which includes effects of heat addition to the flow due to condensation. Two possible limit types of condensation processes are considered. In the nonequilibrium and homogeneous process, the condensate mass fraction is calculated according to classical nucleation and droplet growth rate models. In the equilibrium process, the condensate mass fraction is calculated by assuming an isentropic process. The flow and condensation equations are solved numerical1y by iterative computations. Results under same upstream conditions describe the flow structure, field of condensate, and pressure distribution on airfoil's surfaces. It is found that flow characteristics, such as position and strength of shock waves and airfoil’s pressure distribution, are different for the two condensation processes. Yet, in each case, heat addition as a result of condensation causes significant changes in flow behavior and affects the aerodynamic performance of airfoils.