• Proceeding of EDISON Challenge
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• 2015.03a
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• pp.569-574
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• 2015

지난 수십 년간 유체역학적인 관점에서 곤충이나 새의 움직임을 모방하기 위해 진동하는 익형(pitching airfoil)과 동적 실속에 관한 많은 연구가 진행되어 왔다. 그러나 유동박리가 일어나지 않는 범위 내에서 진동하는 익형의 특성에 대한 연구는 보기 드물다. 또한 기존의 유동박리가 일어나지 않는 영역에서 익형의 진동 현상에 대해 수행된 연구는 수중과 같이 낮은 레이놀즈수에서 수렴되었기 때문에, 공기 중과 같이 높은 레이놀즈수에서 유동현상과 다른 특성을 보여주고 있을 수 있다. 따라서 본 연구는 높은 레이놀즈수에서의 다양한 환산 진동수, 받음각진폭, 익형에 따른 공력특성을 분석하였다. 그 결과, 익형의 진동으로 인한 양력계수의 차이는 작음을 알 수 있었다. 그러나 높은 환산 진동수에서 익형의 항력계수가 감소하는 경향이 나타나며, 이로 인해 높은 환산 진동수에서 수치적으로 추력이 발생할 수 있음을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.8
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• pp.8-18
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• 2003

An experimental study is carried out to investigate the Reynolds number effects on the near-wake of an airfoil oscillating in pitch. An NACA 4412 airfoil is sinusoidally pitched about the quarter chord point between the angle of attack -6$^{\circ}$ and +6$^{\circ}$. A hot-wire anemometer is used to measure the turbulent intensity in the near-wake region of an NACA 4412 airfoil. The freestream velocities of present work are 3.4, 12.4, 26.2 m/s, and the corresponding Reynolds numbers are $5.3{\times}10^4,\;1.9{\times}10^5,\;4.1{\times}10^5$ and the reduced frequency is 0.1. Axial turbulent intensity profiles are presented to show the Reynolds number effects on the near-wake region behind an airfoil oscillating in pitch. All the cases in these measurements show that the turbulent intensities by the change of the Reynolds number are very large at the lowest Reynolds number $R_N=5.3{\times}10^4$; and are small at the other Reynolds number $(R_N=1.9{\times}10^5\;and\;4.1{\times}10^5)$ in the near-wake region. The significant difference of turbulent intensity between $R_N=5.3{\times}10^4,\;and\;1.9{\times}l0^5$ is observed. A critical value of the Reynolds number in the near-wake of an oscillating NACA 4412 airfoil which indicates laminar separation, no separation or turbulent separation exists in the range between $R_N=5.3{\times}10^4\;and\;1.9{\times}10^5$.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.12
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• pp.9-17
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• 2006

An experimental study was carried out to examine the behavior of the unsteady boundary layer. An NACA 0012 airfoil with aspect ratio of 2.7 was set vertically in a test section, which is sinusoidally pitched about the quarter chord. The oscillating amplitude is from -6$^{\circ}$ to +6$^{\circ}$ and the mean angle of attack is 0$^{\circ}$. Surface mounted probes (Glue-on probes) were employed to measure the surface flow of the boundary layer. Measurements were made at free-stream velocities of 1.98, 2.83, and 4.03m/s, and the corresponding Reynolds numbers based on the chord length were 2.3$\times$104, 3.3$\times$104 and 4.8$\times$104, respectively. The reduced frequency is fixed as 0.1 in all cases. The results show that the surface position of minimum shear stress and of boundary layer break-down can be discerned in the Reynolds number between 2.3$\times$104 and 3.3$\times$104.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.12
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• pp.1-8
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• 2006

An experimental study was carried out in order to investigate the influence of Reynolds number on the near-wake of an oscillating airfoil. An NACA 0012 airfoil was sinusoidally pitched at the quarter chord point, and is oscillated over a range of instantaneous angles of attack of $\pm$6$^{\circ}$. An X-type hot-wire probe was employed to measure the near-wake of an oscillating airfoil, and the smoke-wire visualization technique was used to examine the flow properties of the boundary layer. The free-stream velocities were 1.98, 2.83 and 4.03 m/s and the corresponding chord Reynolds numbers were 2.3${\times}10^4$, 3.3$\times$104 and 4.8${\times}10^4$, respectively. The frequency of airfoil oscillation was adjusted to fix a reduced frequency of K=0.1. The results show that the properties of the boundary layer and the near-wake can dramatically be distinguished in the range of Reynolds numbers between 2.3${\times}10^4$ and 3.3${\times}10^4$, on the other hand, it is similar in the cases of Re=3.3$\times$104 and 4.8$\times$104. This is caused by that the unsteady separation point is dramatically delayed in case of Re= 2.3${\times}10^4$.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.7
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• pp.15-25
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• 2003

An experimental. study is carried out to investigate the near-wake characteristics of an airfoil oscillating in pitch. An NACA 4412 airfoil is sinusoidally pitched about the quarter chord point between the angle of attack -6$^{\circ}$ and +6$^{\circ}$. A hot-wire anemometer is used to measure the phase-averaged mean velocities in the near-wake region of an oscillating airfoil. The freestream velocities of present work are 3.4, 12.4, 26.2 m/s, and the corresponding Reynolds numbers are 5.3${\times}10^4$, 1.9${\times}10^5$, 4.l${\times}10^5$, and the reduced frequency is 0.1. Streamwise velocity profiles are presented to show the Reynolds number effects on the near-wake region behind an airfoil oscillating in pitch. All the cases in these measurements show that the velocity defects by the change of the Reynolds number are very large at the lowest Reynolds number $R_N$=5.3${\times}10^4$: and are small at the other Reynolds numbers ($R_N$=1.9${\times}10^5$ and 4.l${\times}10^5$) in the near-wake region. A significant difference of phase-averaged mean velocity between 5.3${\times}10^4$, and 1.9${\times}10^5$ is observed. The present study shows that a critical value of Reynolds number in the near-wake of an oscillating airfoil exists in the range between 5.3${\times}10^4$, and 1.9${\times}10^5$.

• Journal of Advanced Marine Engineering and Technology
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• v.22 no.1
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• pp.16-20
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• 1998

The critical reynolds number in a square-sectional straight duct is investigated experimentally. The experimental study for the air flow in a square-sectional straight duct is carried out to calssify critical Reynolds number on steady flow and unsteady flow. To calssify the critical Reynolds number we obtained velocity waveform by using a hot-wireanemometer and data acquisition system with photocorder.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.2
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• pp.137-145
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• 2008

An experimental study was performed in order to investigate the influence of Reynolds number on the drag coefficient variations of an oscillating airfoil. A NACA 0012 airfoil was sinusoidally pitched at the quarter chord point with an oscillating amplitude of ${\pm}6^{\circ}$. The free-stream velocities were 1.98, 2.83 and 4.03 m/s and the corresponding chord Reynolds numbers were $2.3{\times}10^4$, $3.3{\times}10^4$ and $4.8{\times}10^4$, respectively. The drag coefficient was calculated from the ensemble average velocity measured by an X-type hot-wire probe(X-type, 55R51) in the near-wakes region. In the case of Re=$2.3{\times}10^4$, variation of drag coefficient shows a negative damping (counter-clockwise variation), which implies an unstable state which could be excited by aerodynamic force, whereas the drag coefficient represents the positive damping (clockwise variation) as the Reynolds number increases from Re=$3.3{\times}10^4$ to $4.8{\times}10^4$. Hence, the drag coefficient variations show significant differences between Re=$2.3{\times}10^4$ and $4.8{\times}10^4$이다.

• 한국항공운항학회:학술대회논문집
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• 2005.11a
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• pp.204-208
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• 2005

• 한국가시화정보학회:학술대회논문집
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• 2006.12a
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• pp.59-62
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• 2006

• Proceedings of the Korea Water Resources Association Conference
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• 2010.05a
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• pp.754-758
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• 2010

케이블 교량에서 발생하는 사장케이블의 진동현상에 대한 현상학적 특성을 명확히 이해해야, 사장케이블의 적합한 제진설계가 가능하다. 본 연구에서는 유체의 흐름과 구조물의 진동을 동적으로 연계하여 해석하기 위하여, ADINA의 CFD 및 Structure 코드를 동적으로 연계하는 FSI(Fluid Flow with Structure Interaction) 기법을 이용하였다. 바람으로 인해 이중원형실린더의 풍상측과 풍하측 실린더에서는 와류가 방출되면서 외력이 작용하게 되며, 이러한 공기력은 풍하측 실린더의 고유진동 운동과 함께 와류진동현상을 유발한다. 본 연구에서는 풍하측 실린더의 와류진동 현상의 해석에 주안점을 두었다. 본 연구에서는 흐름의 레이놀즈수와 이중원형실린더에 대한 바람의 입사각을 변화시키며 풍하측 실린더에서 발생하는 와류진동의 크기를 분석하였다. 본 연구결과, 유입풍속 및 바람의 입사각에 따라 이중원형실린더에서 발생하는 일반적인 와류방출현상과 풍하측 실린더에 작용하는 공기력 및 변위양상을 예측할 수 있었다. 특히, 바람의 입사각이 $15^{\circ}$인 경우에는 풍하측 실린더에서 방출되는 와류로 인해 풍하측 실린더에는 비대칭의 공기력이 작용하며, 이는 풍하측 실린더가 2사분면에서 4사분면 방향으로 진동하는 원인이 되는 것으로 판단된다.