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노기덕(K. D. Ro),김광석(K. S. Kim),강명훈(M. H. Kang) 한국마린엔지니어링학회 2006 한국마린엔지니어링학회 학술대회 논문집 Vol.2006 No.-
The flow around a rotating circular cylinder near a plane wall is investigated by the measurement of the lift acting on the cylinder and by the flow visualization using the hydrogen bubble technique in the circulating water tank. The experimental parameters are the rotating direction of the cylinder, the space ratios H/D(H/D=0.05~0.5) between cylinder and plane wall and the velocity ratios α(α=0~±2.0). In the case of clockwise, the lift on the rotating circular cylinder was increased with the reduction of the space ratios and with the velocity ratios, the upper separation point was more shifted in the rotating direction with them. In the case of anticlockwise, the absolute value of the lift on the rotating circular cylinder was increased with the space ratios and with the velocity ratios, the lower separation point was more shifted in the rotating direction with them.
PIV를 이용한 직렬배열에서 2원주 주위의 유동장 특성 연구
노기덕(K. D. Ro),김광석(K. S. Kim),류성진(S. J. Ryu),김낙균(N. G. Kim),박만익(M. I. Park) 한국동력기계공학회 2006 한국동력기계공학회 학술대회 논문집 Vol.- No.-
The Characteristics of the flowfield around two circular cylinders in tandem arrangement was investigated by PIV. Strouhal numbers, velocity vectors and velocity profiles were observed at centre-to-centre space ratios of P/D=1.5, 2.0 and 2.5, and Reynolds number of Re=3.0×10³~5.0×10³. As the results the Strouhal numbers measured in the rear region of the cylinder of wake side were decreased with the space ratios. The flow between two cylinders was almost stagnated and the size of the stagnated region was larger in the close side than in the far side of the front cylinder. The direction of vortex between two cylinders was opposed each other with the small difference(α =±1.0˚) of the attack angle α.
노기덕(K. D. Ro),강명훈(M. H. Kang),공태희(T. H. Kong) 한국동력기계공학회 2005 한국동력기계공학회 학술대회 논문집 Vol.- No.-
The velocity and pressure fields of a ship's propulsion mechanism of the Weis-Fogh type, in which a airfoil moves reciprocally in a channel, are studied in this paper using the advanced vortex method. The airfoil and the channel are approximated by a finite number of source and vortex panels, and the free vortices are introduced from the body surfaces. The viscous diffusion of fluid is represented using the core-spreading model to the discrete vortices. The velocity is calculated on the basis of the generalized Biot-Savart law and the pressure field is calculated from integrating the equation given by the instantaneous velocity and vorticity fields. Two-dimensional unsteady viscose flows of this propulsion mechanism are numerically clarified, and the calculated results agree well with the experimental ones.