• 대한기계학회논문집B
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• 제27권8호
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• pp.1174-1181
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• 2003

The flow around a circular cylinder was controlled by attaching O-rings to reduce drag force acting on the cylinder. Four experimental models were tested in this study; one smooth cylinder of diameter D (D=60mm) and three cylinders fitted with O-rings of diameters d=0.0167 D, 0.05D and 0.067 D with pitches of PPD=2D, 1D, 0.5D and 0.25D. The drag force, mean velocity and turbulence Intensity profiles in the near wake behind the cylinders were measured for Reynolds numbers based on the cylinder diameter in the range of Re$_{D}$=7.8$\times$10$^3$~1.2$\times$10$^{5}$ . At Re$_{D}$=1.2$\times$10$^{5}$ , the cylinder fitted with O-rings of d=0.0167D in a pitch interval of 0.25D shows the maximum drag reduction of about 5.4%, compared that with the smooth cylinder. The drag reduction effect of O-rings of d=0.067D is not so high. For O-ring circulars, as the Reynolds number increases, the peak location of turbulence intensity shifts downstream and the peak magnitude is decreased. Flow field around the cylinders was visualized using a smoke-wire technique to see the flow structure qualitatively. The size of vortices and vortex formation region formed behind the O-ring cylinders are smaller, compared with the smooth cylinder.der.

• 대한기계학회논문집B
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• 제23권7호
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• pp.937-944
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• 1999

The near-wall flow structures of turbulent boundary layer over riblets having semi-circular grooves were investigated experimentally for the drag decreasing ($s^+=25.2$) and drag increasing ($s^+=40.6$) cases. The field of view used for tho velocity field measurement was $6.75{\times}6.75mm^2$ in physical dimension, containing two grooves. One thousand instantaneous velocity fields over the riblets were extracted for each case of drag increase and decrease. For comparison, five hundreds instantaneous velocity fields over a smooth flat plate were also obtained under the same flow conditions. To see the global flow structure qualitatively, the flow visualization was also performed using the synchronized smoke-wire technique. For the drag decreasing case ($s^+=25.2$), most of the streamwise vortices stay above the riblets, interacting with the riblet tips. The high-speed in-rush flow toward the riblet surface rarely influences the flow inside tho riblet valleys submerged in the viscous sublayer. The riblet tips seem to impede the spanwise movement of the longitudinal vortices and induce secondary vortices. The turbulent kinetic energy in the riblet valley is sufficiently small to compensate the increased wetted area of the riblets. In addition, in the logarithmic region, the turbulent kinetic energy are small or almost equal to that of a smooth flat plato. For the drag increasing case ($s^+=40.6$), however, the streamwise vortices move into the riblet valley freely, interacting directly with the riblet inner surface. The penetration of the high-speed in-rush flow on the riblets increases tho skin-friction. The turbulent kinetic energy is increased in the riblet valleys and even in the outer region compared to that over a flat plate.

• 한국항공우주학회지
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• 제34권12호
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• pp.1-8
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• 2006

진동하는 에어포일의 후류에 미치는 레이놀즈수의 영향을 조사하기 위한 실험적 연구를 수행하였다. NACA 0012 에어포일은 1/4 시위를 기준으로 피칭운동을 하고, $\pm$6$^{\circ}$ 내에서 진동하도록 설정하였다. 진동하는 에어포일에서 후류를 측정하기 위하여 2축 열선풍속계가 사용되었고 연선 가시화 기법이 경계층을 관찰하기 위하여 사용되었다. 실험조건에서 자유흐름속도는 1.98, 2.83 그리고 4.03 m/s이며, 이를 근거로 한 레이놀즈수는 각각 $2.3{\times}10^4$, 3.3${\times}10^4$, 4.8${\times}10^4$이다. 모든 경우에 에어포일 진동수는 무차원 진동수 K=0.1에 맞게 조절되었다. 실험 결과, 피칭하는 에어포일의 경계층 및 후류 유동 특성은 레이놀즈수 2.3$\times$104, 3.3$\times$104 사이에서 크게 다르게 나타나며, 레이놀즈수 3.3${\times}10^4$와 4.8${\times}10^4$에서 유사하게 나타난다. 이것은 레이놀즈수 2.3$\times$104에서 비정상 분리가 크게 지연되기 때문이다.