• 한국항공우주학회지
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• 제37권7호
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• pp.615-626
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• 2009

본 논문에서는 전진 비행하는 탠덤로터의 로터 겹침에 의한 간섭효과에 대해 연구하였다. 기 개발된 시간전진 자유후류 모델이 고려된 비정상 패널 코드는 후류와 깃(blade)이 아주 근접한 경우에 불안정성이 발생하였다. 이를 제거하기 위해서 장속도기법을 적용하여 코드를 개선하였다. 개선된 코드를 이용하여 전진 비행하는 탠덤로터의 상호작용에 가장 큰 영향을 미치는 인자인 로터 간격과 전진비에 따른 파라메타 연구를 수행하였다. 공력성능의 비교를 통해 겹침유도동력계수는 일정한 전진비 이후에는 로터 사이의 수평 거리의 영향은 거의 받지 않으며, 수직 거리의 제곱에 반비례하는 것을 알 수 있었다. 또한 전진비가 증가함에 따라 겹침유도동력계수는 증가하다가 감소하는 경향을 보였다.

• 한국항공운항학회지
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• 제19권1호
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• pp.1-6
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• 2011

The free-wing tilt-body aircraft is researched in the flight performance characteristics such as short take-off and landing capability, and reduced sensitivity to gust and center of gravity (CG) change. Due to the main wing separating from the fuselage, the high tiltable empennage, and the stub-wing strongly influencing from the propeller wake, the resulting vehicle aerodynamics and flight dynamics are quite different from those of a conventional fixed-wing aircraft. Using the governing flight dynamics model was studied previously, all of speed and body tilt angle is simulated to determine the flight envelope by a non-linear 3-DOF flight simulation analysis. Though flight performance and trimmability are studied, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics that distinguishes free-wing tilt-body aircraft from the conventional aircraft.

• 한국유체기계학회 논문집
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• 제3권2호
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• pp.15-23
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• 2000

The present work describes the prediction method for the unsteady flow field and the acoustic pressure field of a ducted axial fan. The prediction method is comprised of time-marching free-wake method, acoustic analogy, and the Kirchhoff-Helmholtz BEM. The predicted sound signal of a rotor is similar to the experiment one. We assume that the rotor rotates with a constant angular velocity and the flow field around the rotor is incompressible and inviscid. Then, a time-marching free-wake method is used to model the fan and to calculate the flow field. The force of each element on the blade is calculated by the unsteady Bernoulli equation. Lowson's method is used to predict the acoustic source. The newly developed Helmholtz-Kirchhoff BEM lot thin body is used to calculate tile sound field of the ducted fan. The ducted fan with 6 blades is analysed and the sound field around the duct is calculated.

• International Journal of Fluid Machinery and Systems
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• 제2권3호
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• pp.197-205
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• 2009

Since large-scale commercial wind turbine generator systems such as MW-class wind turbines are becoming widely operated, the vibration and distortion of the blade are becoming larger and larger. Therefore the soft structure design instead of the solid-design is one of the important concepts to reduce the structural load and the cost of the wind turbine rotors. The objectives of the study are development of the fluid-structure coupled analysis code and evaluation of soft rotor-blade design to reduce the unsteady structural blade load. In this paper, fluid-structure coupled analysis for the HAWT rotor blade is performed by free wake panel method coupled with hinge-spring blade model for the flapwise blade motion. In the model, the continuous deflection of the rotor blade is represented by flapping angle of the hinge with one degree of freedom. The calculation results are evaluated by comparison with the database of the NREL unsteady aerodynamic experiment. In the analysis the unsteady flapwise moments in yawed inflow conditions are compared for the blades with different flapwise eigen frequencies.

• 대한조선학회논문집
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• 제42권6호
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• pp.593-600
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• 2005

The finite volume based multi-block RANS code, WAVIS developed at KRISO, is used to simulate the turbulent flow field around the KRISO container ship (KCS) and the modified KRISO tanker (KVLCC2M). The realizable k-$\varepsilon$ turbulence model with a wall function is employed for the turbulence closure. The free surface flow with and without propeller is mainly investigated for the KCS and the double model flow is concerned for the KVLCC2M which is obliquely towed in still water. The computed results are compared with the experimental data provided by CFD Tokyo Workshop 2005 in terms of wave profiles, hull surface pressure and wake distribution with and without propeller for the HCS and wake distribution and hydrodynamic forces and moments with various drift angles for the KVLCC2M.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2010년도 춘계학술대회
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• pp.389-391
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• 2010

자유수면에 접한 원형실린더는 후류유동에 변화를 초래한다. 이를 위해 희류수조의 수면하 깊이를 변화시키며 $Re=1.0\times10^3$에서 순간유동장을 계측하여 실험을 통하여 그 영향을 조사하였다. 계측된 결과는 상호상관 PIV기법을 이용하여 원형실린더의 2차원 유동특성을 알아보기 위하여 상호 비교하였다. 자유수면에 의한 원형실린더 주변유동은 후류에 영향을 미친다. 특히 d=l.0D의 경우에 있어서 경계층은 전체 영역에 걸쳐 분포하였다. 원형실린더의 박리점과 경계층은 수심의 깊이에 따라 제어가 가능하였다.

• 한국항해항만학회지
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• 제34권5호
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• pp.331-336
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• 2010

원형실린더가 균일한 유입유동에서 자유수면 으로부터 깊이를 달리했을 경우 박리점, 경계층 및 칼만 와열의 주기 등의 변화로 인하여 시스템 전체 에너지에 변화를 초래한다. 본 연구에서는 원형실린더의 침수 깊이를 변화시키며 $Re=1.0{\times}10^3$에서 유동장을 계측하였다. 2차원 그레이 레벨 상호상관 PIV기법을 이용하여 원형실린더 주위의 유동특성을 알아보기 위하여 상호 비교하는 방법을 적용하였다. 자유수면의 점성과 마찰에 의해 발생하는 원형실린더 주변유동은 경계층을 변화시키고 후류유동에 교란을 일으킨다. 특히, 몰수체의 깊이가 d=1.0D의 경우에 있어서 경계층의 변화가 후류로 길게 형성되었다. 원형실린더의 깊이가 d=1.5D에서부터 자유수면의 영향이 감소하고 칼만 와열이 발달하였다.

• 대한기계학회논문집B
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• 제30권2호
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• pp.136-143
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• 2006

A particle image velocimetry (PlV) technique has been applied to measure the quantitative flow field characteristics behind a road vehicle with/without an air spoiler attached on its trunk and to estimate its effect on the wake. A vehicle model scaled in the ratio of 1/43 is set up in the mid-section of a closed-loop water tunnel. The Reynolds number based on the vehicle length is $10^5$. To investigate the three-dimensional structure of the recirculation zone and vortices, measurements are carried out on the planes both parallel and perpendicular to the free stream, respectively. The results show significant differences in the recirculation region and the vorticity distributions according to the existence of the air spoiler. The focus and the saddle point, appearing just behind the air spoiler, are disposed differently along the spanwise direction. Regarding the streamwise vortices, the air spoiler produces large wing tip vortices. They have opposite rotational directions to C-pillar vortices which are commonly observed in case that the air spoiler is absent. The wing tip vortices generate the down-force and as a result, they can make the vehicle more stable in driving.

• Wind and Structures
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• 제26권5호
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• pp.317-329
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• 2018

Wake characteristics of the flow over a finite square prism at different incidence angles were experimentally investigated using an open-loop wind tunnel. A finite square prism with a width D = 15 mm and a height H = 7D was vertically mounted on a horizontal flat plate. The Reynolds number was varied from $6.5{\times}10^3$ to $28.5{\times}10^3$ and the incidence angle ${\alpha}$ was changed from $0^{\circ}$ to $45^{\circ}$. The ratio of boundary layer thickness to the prism height was about ${\delta}/H=7%$. The time-averaged velocity, turbulence intensity and the vortex shedding frequency were obtained through a single-component hotwire probe. Power spectrum of the streamwise velocity fluctuations revealed that the tip and base vortices shed at the same frequency as that ofspanwise vortices. Furthermore, the results showed that the critical incidence angle corresponding to the maximum Strouhal number and minimum wake width occurs at ${\alpha}_{cr}=15^{\circ}$ which is equal to that reported for an infinite prism. There is a reduction in the size of the wake region along the height of the prism when moving away from the ground plane towards the free end.

• 대한기계학회논문집B
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• 제25권7호
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• pp.915-922
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• 2001

A new phase-average technique using instantaneous velocity fields obtained by a PIV method has been developed. The technique tracks vorticity centers and estimates the value of circulation for a chosen domain. The locations of vortex-centers and the magnitudes of circulation are matched together then showing a sine wave feature due to the periodic vortex shedding from the circular cylinder. Ensemble averaged and phase averaged velocity fields are successfully measured for the circular cylinder wake where Reynolds number is 3900 based on free stream velocity and cylinder diameter. The convection velocities of the vortices center and the vortex shedding frequency were measured by a single hot-wire probe.