• 대한기계학회논문집
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• 제19권1호
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• pp.240-250
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• 1995

A CPM (computational preston tube method) was developed to measure wall shear stress in a transitional boundary layer on a flat plate using Preston tubes. Correlation for the displacement factor of Preston tubes was improved for a CPM to be used in the transitional boundary layer. The distribution of skin-friction coefficient was reasonably predicted in the uniform free stream of 3.1% turbulence intensity. Reasonable and accurate estimation of displacement factor of Preston tubes was found to be of crucial importance for the CPM, especially in the laminar boundary layer. The mean velocity profiles of the boundary layer on the plate were also measured and presented.

• 대한기계학회논문집
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• 제18권7호
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• pp.1873-1880
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• 1994

Fully developed turbulent flow in a circular pipe and laminar boundary layer on a flat plate were measured to develop a measuring technique of the wall sheat stress using Preston tubes. New empirical formulas to extimate displacement factor of Preston tube obtained through the present study. The displacement factor for turbulent flow was considerably different from that for the laminar flow. Measured wall shear stress was not pretty dependent on the displacement factor for Preston tubes in the inertia sublayer of turbulent boundary layer, however was considerably affected in the laminar boundary layer. Measuring error of skin friction using the CPM technique was 3% for turbulent and 5% for thin laminar boundary layers.

• Ecology and Resilient Infrastructure
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• 제4권4호
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• pp.207-215
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• 2017

하도의 흐름 저항, 측벽 보정, 유사량, 하도 침식과 퇴적, 하도 설계 등의 수리학적 문제는 하상전단응력의 분포와 밀접한 관계가 있으나 하상전단응력 분포를 측정하는 것은 쉽지 않다. 본 연구에서는 간편하게 하상전단응력을 측정할 수 있는 프레스톤튜브를 이용하여 복단면의 하도의 하상전단응력 분포를 측정하고 수심비에 따른 전단응력분포 특성을 고찰하였다. 이를 위해 프레스톤튜브를 제작하여 검정실험을 통해 검정식을 개발하였다. 실험은 5가지 수심비 조건에 대해서 수행하여 전단응력분포를 측정하였다. 복단면 하도의 전단응력분포 특성은 기존 실험연구와 대체로 일치하였으며, 레이놀즈수 증가로 발생하는 전단응력의 변동성, 주수로 전단응력의 변곡점 형성, 홍수터 접합부 부근 전단응력 분포 특성 등에서 차이점을 확인하였다. 본 연구를 통해 프레스톤튜브를 이용한 하상전단응력측정 적용성을 확인하였으며 레이놀즈수와 수심비에 따른 복단면 하도의 전단응력분포 특성을 제시하였다.

• 대한기계학회논문집
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• 제16권12호
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• pp.2349-2357
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• 1992

본 연구에서는 일정한 조도의 거친 평판이 갑자기 매끈한 평판으로 변할 때 (Fig.1 참고) 평판 위에서 발달하는 난류경계층에 관하여 연구하였다. 이때 하류에 서 난류 경계층은 위에서 설명했듯이 완전히 발달한 난류 경계층과는 상당히 다르다. 특히 대부분의 난류 모델은 완전히 발달된 평형상태의 경계층에서의 실험자료를 이용 하여 개발되었기 때문에 이러한 과도 구역에서 합리적으로 적용되기가 어렵다. 과도 구역에서 평균속도와 난류 특성치를 체계적으로 계측하기 위해서는 전단응력을 직접 계측하는 것이 중요하다. 그러나 아직 전단응력을 직접 계측한 연구는 없는 실정이 다. 본 논문에서는 최근에 제안된 CPM(computational preston tube method)를 이용 하여 과도지역에서 전단응력을 직접 측정하여 난류 경계층의 구조를 연구하였다.

• 대한기계학회논문집B
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• 제20권5호
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• pp.1689-1699
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• 1996

A study on the transitional boundary layer with arbitrary pressure gradient under various upstream conditions is very important for engineering applications like the performance predictions of the turbomachineries under various and strong disturbances. Experimental data on the transitional boundary layer for real cascades of the turbomachinery are rare because of difficulties in boundary layer experiments. Flow on NACA0012 airfoil is more similar to the real case than that on the flat plate with which many researches are done. The data of the transitional flow on the airfoil could be used to verify or to develop a turbulence model for numerical simulations. The experiment was performed with two cases of Reynolds number at a=0$^{0}$ and one case of Reynolds number at a=5$^{0}$ . The measured data are the transition length and the wall shear stresses. These two characteristic values are measured within 25%~90% of the airfoil chord by Computation Preston tube Method(CPM) proposed by Nitsche et al.(1983). At a=0$^{0}$ , transition occured at 70% and 55% of chord length when R $e_{c}$=6*10$^{5}$ and 8* 10$^{5}$ , respectively. It started when R {\theta}=500 regardless of R $e_{c}$, and ended when R {\theta}=750, and 850 respectively. The transition length was 15~20% of the chord length. At a=5$^{0}$ (R $e_{c}$=6*10$^{5}$ ), boundary layer on the pressure side does not undergo transition, but on the suction side transition occured at .chi.$_{c}$/c=0.16 and ended at .chi.$_{c}$/c=0.22.c//c=0.22./c=0.22.c//c=0.22.

• 대한기계학회논문집B
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• 제26권5호
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• pp.685-694
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• 2002

Effects of wake-passing orientation and frequency on the wake-induced boundary layer transition on a NACA0012 airfoil are investigated. The wakes are generated by rotating cylinders clockwise (CW) and counterclockwise (CCW) around the airfoil. Time- and phase-averaged streamwise mean velocities and turbulent fluctuations are measured with a single hot-wire probe. Wall skin frictions are estimated by the Computational Preston Tube Method (CPM). The pressure distribution on the airfoil is different according to the wake-passing orientation and frequency. Turbulent patches are generated in the laminar boundary layer due to the passing wake and the boundary layer becomes temporarily transitional. The transition process is significantly affected by the pressure gradient and the turbulent patches. For the receding wake, the turbulent patches propagate more rapidly than those for the approaching wake because adverse pressure gradient becomes larger. As the frequency increases, onset location of transition moles upstream and the boundary layer near the trailing edge becomes more transitional.

• Journal of Mechanical Science and Technology
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• 제14권11호
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• pp.1305-1318
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• 2000

The local wall shear stress in transitional boundary layer was estimated from the near-wall mean velocity data using the principle of Computational Preston Tube Method(CPM). The previous DNS and experimental databases of transitional boundary layers were used to demonstrate the accuracy of the method and to provide the applicable range of wall unit y(sup)+. The skin friction coefficients predicted by the CPM agreed well with those from previous studies. To reexamine the applicability of CPM, near-wall hot-wire measurement were conducted in developing transitional boundary layers on a flat plate with different freestream turbulence intensities. The intermittency profiles across the transitional boundary layers were reasonably obtained from the conditional sampling technique. An empirical correlation between the representative intermittency near the wall and free parameter K$_1$of the extended wall function of CPM has been newly proposed using the present and other experimental data. The CPM has been verified as a useful tool to measure the wall shear stress in transitional boundary layer with reasonable accuracy.

• 대한기계학회논문집B
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• 제22권9호
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• pp.1335-1348
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• 1998

Flow characteristics in transitional boundary layers on a flat plate were experimentally investigated under three different freestream conditions i. e. uniform flow with 0.1 % and 3.7% freestream turbulent intensity and cylinder-wake with 3.7% maximum turbulent intensity. Instantaneous streamwise velocities in laminar, transitional and turbulent boundary layers were measured by I-type hot-wire probe. For estimation of wall shear stresses on the flat plate, measured mean velocities near the wall were applied to the principle of Computational Preston Tube Method (CPM). Distributions of skin friction coefficients were reasonably predicted in all developed boundary layers. Intermittency profiles, which were estimated using Conditional Sampling Technique in transitional boundary layers, were also consistent with previously published data. It was predicted that the incoming turbulent intensity had more influence on transition onset point and transition process than freestream turbulent intensity existed just over the transition region. It was also confirmed that non-turbulent and turbulent profiles in transitional boundary layers could not be simply treated as Blasius and fully turbulent profiles.

• 한국수자원학회:학술대회논문집
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• 한국수자원학회 2016년도 학술발표회
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• pp.445-445
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• 2016

급변하는 개수로 흐름에서 발생하는 바닥전단응력의 분포는 하천구조물 설계에 있어 매우 중요한 요소이다. 하천 구조물 중 호안에 대한 하천설계기준 '설계편 제 24장 호안'에는 호안 설계에 대한 일반적인 사항이 제시 되어 있으나, 구체적인 소류력 또는 유속에 대한 기준, 각 호안공법들의 안정성을 평가하기 위한 시험법 등에 대한 구체적인 기준이 부족한 상황이다. 소류력 측정방법에는 간접측정법과 직접측정법이 있다. 간접측정법에는 Reach-Average공식, Reynolds Stress, TKE공식 (Turbulent Kinetic Energy)이 있고 직접측정법에는 Shear Meter, Preston Tube 등이 있다. 본 연구에서는 바닥전단응력을 직접 측정할 수 있는 1차원 소류력 측정장치를 개발하고, 최대유속 5m/s 가변형 고속수로 실험을 통하여 Reach-Average 공식, Reynolds Stress, TKE 공식으로 산정한 바닥전단응력 값과 1차원 소류력 측정장치 값을 비교 분석하였다. 실험케이스는 총 3개로, 22.42???, 30.00???, 41.00??? 유량을 사류이면서 난류인 상태로 실험을 수행하였다. 분석 결과, 본 연구에서 개발한 1차원 소류력 측정장치의 측정값은 TKE공식과 약 2.3% 차이가 났으며, Reach-Average공식과 약 8.1%, Reynolds Stress는 약 22.1% 차이가 났다. 즉, 본 연구에서 개발한 1차원 소류력 측정장치는 유속 범위(1m/s ~1.6m/s )에서 TKE공식을 이용한 바닥전단 응력과 가장 근사하게 나타나는 것으로 분석되었다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.687-690
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• 2002

Multimode boundary-layer transition on a NACA0012 airfoil is experimentally investigated under periodically passing wakes and the moderate level of free-stream turbulence. The periodic wakes are generated by rotating circular cylinders clockwise or counterclockwise around the airfoil. The free-stream turbulence is produced by a grid upstream of the rotating cylinder, and its intensity(Tu) at the leading edge of the airfoil is $0.5\;or\;3.5\;{\%}$. The Reynolds number ($Re_c$) based on chord length (C) of the alrfoil is $2.0{\times}10^5$, and Strouhal number ($St_c$) of the passing wake is about 0.7. Time- and phase-averaged streamwise mean velocities and turbulence fluctuations are measured with a single hot-wire probe, and especially, the corresponding wall skin friction is evaluated using a computational Preston tube method. The wake-passing orientation changes pressure distribution on the airfoil in a different manner irrespective of the free-stream turbulence. Regardless of free-stream turbulence level, turbulent patches for the receding wakes propagate more rapidly than those for the approaching wake because adverse pressure gradient becomes larger. The patch under the high free-stream turbulence ($Tu=3.5{\%}$) grows more greatly in laminar-like regions compared with that under the low background turbulence ($Tu=0.5{\%}$) in laminar regions. The former, however, does not greatly change the original turbulence level in the very near-wall region while the latter does it. At further downstream, the former interacts vigorously with high environmental turbulence inside the pre-existing transitional boundary layer and gradually lose his identification, whereas the latter keep growing in the laminar boundary layer. The calmed region is more clearly observed under the lower free-stream turbulence level and for the receding wakes. The calmed region delays the breakdown further downstream and stabilizes more the boundary layer.