• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.93-96
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• 2012

경계층이란 유체와 물체 표면의 마찰로 인해 생성되는 층을 말한다. 경계층은 두께에 따라 층류 경계층, 천이 경계층, 난류 경계층으로 나누어진다. 레이놀즈 수 크기에 따라 경계층은 몇 가지의 층으로 구분되어 진다. 이 계산에서는 경사진 평판 위에서 유동의 현상들이 어떻게 일어나는지 확인하였다. 또한, 경사가 없는 평판위에서 velocity profile과 Blasius solution을 비교하였고, 평판의 뒤쪽에 격자의 간격이 넓음으로 큰 오차가 발생하게 됨을 알 수 있었다.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.113-116
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• 2012

본 연구에서는 마하수 변화에 따른 층류유동 변화를 살펴보았다. 해석 프로그램은 EDISON_CFD를 이용하고, EDISON_CFD에서 사용한 수치기법과 Scheme에 대해서 언급한다. CFD기법을 이용하여 해석한 결과를 경계층조건의 이론 해석방법인 Blasius Boundary Layer와 비교하였다. 각 요소마다 해석한 결과를 통하여 층류 경계층의 특성을 살펴보았다. 그 결과 마하수 증가에 따른 평판의 온도 증가와 밀도 감소가 경계층을 선형적으로 증가시키는 것을 보았다. 또한 마하수 증가에 따른 점성계수의 증가를 살펴봄으로서 층류유동에서 마하수의 증가는 점성에 의한 운동량 확산을 증가시킨다는 것을 보았다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1165-1172
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• 2009

The laminar boundary layer along a streamwise corner formed by two flat plates intersecting at right angle is measured by using Particle Image Velocimetry(PIV) technique. The free stream velocity ranges from 2.96m/s to 3.0m/s. The angle of incidence of the corner is set to 1.2 degree providing slightly favourable pressure gradient to ensure a laminar flow in the corner region. A round shape leading edge is used and the length of the model is about 1000mm. In the bisector plane, the measurement data show separation type velocity profiles having an inflection point which is a typical characteristic of laminar corner boundary layers. As the distance away from the bisector plane increases, velocity profiles are found to change into the Blasius profile. The change completes around half length of the boundary layer thickness in the bisector plane away from the bisector plane along the plate. In the bisector plane, the growth characteristic of the boundary layer thickness and the approximate similarity of velocity profiles are confirmed from the measurement data.

• Journal of the Korean Society of Marine Environment & Safety
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• v.24 no.1
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• pp.92-100
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• 2018

Vortical systems are considered a main feature to sustain turbulence in a boundary layer through interaction. Such turbulent structures result in frictional drag and erosion or vibration in engineering applications. Research for controlling turbulent flow has been actively carried out, but in order to show the effect of vortices in a turbulent boundary layer, it is necessary to clarify the mechanism by which turbulent energy is transferred. For this purpose, it is convenient to demonstrate and capture phenomena in a laminar boundary layer. Therefore, in this study, the interactions of disturbed flow around a hemisphere on a flat plate in laminar flow were analyzed. In other words, a street of hairpin vortices was generated following a wake region formed after flow separation occurred over a hemisphere. Necklace vortices surrounding the hemisphere also appeared due to a strong adverse pressure gradient that brought high momentum fluid into the wake region thereby leading to an increase in the frequency of hairpin vortices. To mitigate the effect of these necklace vortices, local suction control was applied through a hole in front of the hemisphere. Flow visualization was recorded to qualitatively determine flow modifications, and hot-film measurements quantitatively supported conclusions on how much the power of the hairpin vortices was reduced by local wall suction.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.16-23
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• 2006

A study on the boundary layer behavior of an NACA 0012 airfoil at low Reynolds numbers was investigated in order to gain knowledge of a boundary layer that might be employed in a turbine blade and MAVs. A hot-wire anemometer was used to measure the boundary layer of an NACA 0012 airfoil at static angles of attack ${\alpha}$=$0^{\circ}$, $3^{\circ}$, and $6^{\circ}$, and Reynolds Numbers Re=$2.3{\times}10^4$, $3.3{\times}10^4$, and $4.8{\times}10^4$. The results of this study show that the laminar boundary layer on the airfoil surface is attached to the surface at ${\alpha}$=$0^{\circ}$, and the laminar separation of the boundary layer on the airfoil surface occurs at ${\alpha}$=$3^{\circ}$. Furthermore, the reattachment of the boundary layer in the present study occurs for the cases of Re=$3.3{\times}10^4$ and Re=$4.8{\times}10^4$at ${\alpha}$=$6^{\circ}$.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.14 no.4
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• pp.1533-1539
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• 2013

In the present study, we compared the theory with CFD data about the boundary layer thickness, displacement thickness and momentum thickness. According to the freestream velocity, larminar and turbulent is decided and affect to the flow patterns around the airfoil The boundary layer thickness, displacement thickness and momentum thickness affect to the aerodynamic characteristics of the airfoil(e.g. lift, drag and pitching moment). The separation point is affected by varying angle of attack. In the present study, we used the Joukowski airfoil(c=1), and NACA0012 airfoil was used at CFD. The chord Reynolds number is $Re_c$=3,000, 700,000, respectively and the freestream velocity is 0.045, 10 m/s, respectively. In this paper, the data was a good agreement with that of experimental results, so we can analyze the various airfoil models.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1055-1065
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• 2009

In this study, stability analysis of boundary layers on airfoils is performed by using parabolized stability equations(PSE). Boundary layer edge conditions are obtained by compressible inviscid flow calculations. Mean velocity and temperature profiles of the laminar boundary layer are obtained by solving compressible boundary layer equations in generalized curvilinear coordinates with fourth order accuracy in the wall normal direction. Laminar mean flow profiles are used as input data for PSE to investigate growth rates of disturbances and stability characteristics. For the cases of boundary layer on NACA0012 and HSNLF(1)-0213 airfoils at Mach number 0.5, growth rates with respect to disturbance frequencies and profiles of disturbance amplitude are investigated. The effect of angle of attack on stability characteristics are examined at both upper and lower surfaces. The neutral stability curves, effect of Mach number and effect of airfoil section shapes are also analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.477-483
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• 2016

Velocity profiles of laminar, transition and turbulent boundary layers were investigated by using Particle Image Velocimetry(PIV) measurements on the flat plate at Mach 2.96. The Schlieren visualization and PIV measurements are also used to confirm whether the oblique shock wave generated from the leading edge affects the flow field over the flat plate. The laminar velocity profile measured from the experiment was well matched with the compressible Blasius solution. The velocity profile of the transition boundary layer was well correlated with the theoretical turbulent velocity profile from near the wall and the transition began from Re = $1.41{\times}106$. For the turbulent boundary layer, considering compressibility effects, the Van Driest-transformed velocity satisfies the incompressible log-law. It is found that the log region is extended farther in the wall-normal direction compared to the log region in incompressible boundary layer.

• Proceeding of EDISON Challenge
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• 2014.03a
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• pp.539-543
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• 2014

임의의 물체가 유체 내에서 운동하거나 정지해 있을 때 유체에 의해서 운동에 방해가 되는 힘을 형상저항이라고 한다. 형상저항은 레이놀즈수에 의한 경계층의 흐름형태에 따라 변화하며, 경계층의 흐름형태는 레이놀즈수가 $10^5$보다 작은 경우 층류로, 그 이상의 경우 난류로 나타난다. 본 연구에서는 유체 내에 물체가 정지해 있을 경우 조도에 따른 형상저항의 변화를 알아보기 위해 각기 다른 조도를 가진 실린더를 모델링해 EDISON_CFD을 이용하여 전산 해석을 하였다. 실린더의 표면에 파장의 주기와 진폭, 층류와 난류 영역에서의 항력계수의 변화에 대해 검토하였다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.14 no.4
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• pp.937-944
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• 1990

본 연구에서는 파이프내에 부분 오리피스판을 장착하여 이 장애벽 전후에서 발생하는 유동현상을 박리 전단층의 유동구조와 재부착 경계층을 중심으로 실험적으로 연구하였다. 측정방법으로 유동의 속도장변화를 구하기 위하여 NMR 위상 영상법을 사용하였고, 과망간산칼륨을 염료로 가시화 실험을 수행하여 그 결과를 비교 검토하였 다.