• 한국항공운항학회지
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• 제30권2호
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• pp.1-6
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• 2022

Recently, the development of UAM, which was named by NASA as an alternative to solve the traffic and environmental problems caused by the rapidly progressing urbanization. When designing UAM, the location of lift fans greatly affects the core technology of the eVTOL type, distributed electric propulsion technology and aerodynamic performance of the vehicle. In this paper, a hybrid UAM model was designed using OpenVSP, an open source aircraft configuration modeling program, and aerodynamic analysis was performed according to the lift fans position change by the vortex lattice method. As a result, it is confirmed that the flight parameters and trailing wakes are stable by fixing the lift fan with the state rotated 0° to the flow direction of the aircraft during cruise flight. Also, OpenVSP is a suitable tool to be used in aircraft configuration modeling and design.

• Wind and Structures
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• 제34권1호
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• pp.91-100
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• 2022

Numerical simulations are conducted to investigate the uniform flow (UF) and sinusoidal streamwise flow (SSF) over an oscillating 5:1 rectangular cylinder with harmonic heaving motion at initial angles of attack of α = 0° and 3° using two-dimensional, unsteady Reynolds-averaged Navier-Stokes (URANS) equations. First, the aerodynamic parameters of a stationary 5:1 rectangular cylinder in UF are compared with the previous experimental and numerical data to validate the capability of the computationally efficient two-dimensional URANS simulations. Then, the unsteady flow field and aerodynamic forces of the oscillating 5:1 rectangular cylinder in SSF are analysed and compared with those in UF to explore the effect of SSF on the rectangular cylinder. Results show that the alternative vortex shedding is disturbed by SSF both at α = 0° and 3°, resulting in a considerable decrease in the vortex-induced force, whereas the unsteady lift component induced by cylinder motion remains almost unchanged in the SSF comparing with that in UF. Notably, the strong buffeting forces are observed at α = 3° and the energy associated with unsteady lift is primarily because of the oscillations of SSF. In addition, the components of unsteady lift induced by the coupling effects of SSF and cylinder motion are discussed in detail.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 춘계학술대회논문집
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• pp.1020-1025
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• 2002

This paper exploits how vortex noise is generated around a cylinder. This is done by utilizing an acoustic holography. In this experiment. compressed air was Infected to tile cylinder through a hose. Therefore, major noise sources were at a hose end as well as around the cylinder： vortex shedding noise. The holography results show a resultant noise picture there it is not easy to clearly sort out the shedding noise and what is generated at the end of the tube. We attempted to separate those noise by the method we developed : contribution analysis scheme. The method, in fact, was found to be efficient and practical to separate the noise field into independent noise sources. The highlights of the results are. we believe, that lift and drag noise picture are now available. This procedure does not limit its application. therefore we may use this to visualize any noise field that we want to understand.

• 대한기계학회논문집B
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• 제36권12호
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• pp.1161-1169
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• 2012

지면효과를 받는 3차원 대칭단면 날개(NACA0015)의 공력특성과 끝단와(wing-tip vortex)의 거동에 관하여 수치적 연구를 수행하였다. 날개가 지면에 근접함에 따라 공기 역학적 특성과 끝단와의 거동은 두 가지 상이한 현상(지면효과와 벤츄리효과)에 의하여 영향을 받는다. 지면효과는 양력을 증가시키며 항력을 감소시켜 공기역학적 특성을 향상시키는 반면 벤츄리효과는 음의 양력을 만들고 항력을 급격히 증가시킨다. 대칭형 익형은 받음각에 따라 이러한 현상이 모두 나타난다. NACA0015의 경우 받음각이 4도 보다 작은 경우 벤츄리효과가 지배적이며 받음각이 이 보다 큰 경우 지면효과가 지배적으로 나타난다. 특이하게 4도에서는 이 두 가지 현상이 모두 나타났다. 벤츄리효과가 지배적인 경우 지면과 날개 사이의 흡입현상의 증가로 인하여 끝단와는 날개의 안쪽으로 끌려 들어오는 반면 지면효과가 지배적인 경우 끝단와는 날개의 바깥쪽으로 밀려나가는 현상을 알 수 있었다.

• 대한기계학회논문집B
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• 제20권5호
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• pp.1649-1660
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• 1996

The flow around a circular cylinder was controlled by an acoustic excitation issued from a thin slit along the cylinder axis. The static pressure distributions around the cylinder wall and flow characteristics in the near wake have been measured. Experiments were performed under three cases of Reynolds number, 7.8 * 10$\^$4/, 2.3 * 10$\^$5/ and 3.8 * 10$\^$5/. The effects of excitation frequency, sound pressure level and the location of the slit were examined. Data indicate that the excitation frequency and the slit location are the key parameters for controlling the separated flow. At Re$\_$d/, = 7.8 * 10$\^$4/, the drag is reduced and the lift is generated to upward direction, however, at Re$\_$d/, =2.3 * 10$\^$5/ and 3.8 * 10$\_$5/, the drag is increased and lift is generated to downward direction inversely. It is thought that the lift switching phenomenon is due to the different separation point of upper surface and lower surface on circular cylinder with respect to the flow regime which depends on the Reynolds number. Vortex shedding frequencies are different at upper side and lower side. Time-averaged velocity field shows that mean velocity vector and the points of maximum intensities are inclined to downward direction at Re$\_$d/ = 7.8 * 10$\^$4/, but are inclined to upward direction at Re$\_$d/ = 2.3 * 10$\^$5/.

• 한국항공우주학회지
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• 제37권8호
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• pp.729-736
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• 2009

벌새(Selasphorus rufus)의 날갯짓 운동에 의한 양력발생 및 추력발생 메커니즘을 이해하고자 2차원 수치해석을 수행하였다. 날갯짓 운동의 궤적은 풍동 실험에서 관찰된 결과를 모델링하여 해석하였다. 비행속도에 따라 날갯짓 운동 궤적이 달라지고, 그 결과 양력 및 추력의 발생 메커니즘이 변화하는 것을 알 수 있었다. 본 연구에서는 이를 통하여 비행속도를 저속비행과 고속비행으로 구분하여 물리적인 이해를 하고자 하였다. 양력발생의 경우에는 기존의 날갯짓 비행의 주된 양력발생 메커니즘인 앞전와류효과(Leading Edge Vortex Effect), 실속지연(Delayed Stall), 후류포착(Wake capture)등의 메커니즘을 확인하였으며, 벌새에서 유일하게 관찰되는 Upstroke에서의 양력발생 메커니즘을 유동특성 분석을 통하여 확인하였다. 추력발생의 경우에는 벌새의 골격 구조, 와류형성 및 압력구배에 따른 합력 성분의 분해를 통하여 이해할 수 있었다.

• 대한기계학회논문집B
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• 제22권5호
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• pp.573-583
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• 1998

Effects of the oscillating incoming flow on vortex shedding and lock-on behind a square cylinder are investigated using numerical simulations at a Reynolds number of 100. Vortex shedding occurred at low forcing frequencies of the incoming flow similar to the natural vortex shedding. As the forcing frequency further increases, the shedding frequency decreases to the half of the forcing freqnency. For a sufficiently large frequency, vortex shedding returns to the natural vortex shedding irrespective of the forcing amplitude. Also, the lock-on region becomes wider with higher forcing amplitudes. The phase diagram between the drag and lift shows a simple periodic behavior in the lock-on region, while a complicated periodic phase relation is observed when there is no lock-on.

• 한국산학기술학회논문지
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• 제21권4호
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• pp.446-451
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• 2020

전열관군으로 이루어진 열교환기에서 유동에 따른 진동은 전열 관군 배관의 파손을 유발할 수 있어서 열교환기에서 유동 유발 진동 특성을 규명할 필요가 있다. 본 연구는 전열 관군의 원관에서 입구의 유속이 일정한 경우와 주기적인 변동이 있는 경우에 대하여 시간에 따라 전열 관군 원관 1, 10 그리고 마지막 19번 원관에서 와류의 시간 변동 특성을 살펴보고 양력의 시간 변화 특성과 PSD 특성을 분석하여 전열 관군 원관에서 전방류의 주기적인 속도 변동에 따른 유동 특성을 규명하였다. 일정 입구 유속의 경우는 칼만 와류가 후류에 있는 원관의 유동에 영향을 미치고 있고 후류의 전열관군과 전방의 전열관군에서의 와류는 다소 시간적인 차이를 보여주지만 같은 주기의 칼만 와류를 발생하고 있음을 관찰할 수 있었다. 주기적인 입구 유속의 경우는 전열 관군에서 와류가 강한 유동이 흐르다가 유속이 줄어들 때는 와류가 약한 유동이 흐르는 것이 반복됨을 알 수 있다. 일정 입구 유속의 경우는 양력의 PSD로 살펴본 결과 주파수는 37.25Hz이며 19번 원관의 경우는 18.63Hz와 50Hz 근방에서 주파수가 관찰 되었다. 주기적인 입구 유속의 경우는 37.25Hz와 속도 주기인 18.63Hz에서 주된 주파수 특성을 보여주었다. 마지막 원관인 19번 원관은 20Hz에서 50Hz 사이에서 많은 피크 주파수를 관찰할 수 있었다.

• International Journal of Aeronautical and Space Sciences
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• 제6권2호
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• pp.33-45
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• 2005

The 1/9-scale model of a fighter-type configuration was tested in the Micro-Craft 8ft ${\times}$ 12ft wind tunnel facility. An abrupt lift dump was found at a certain range of angle of attack under the pre-scheduled approach configuration. To avoid a probable unsatisfactory flight behavior due to the lift dump, various aerodynamic devices were suggested. Extensive tests applying the cutoff leading edge flaps, boundary layer fences, saw tooth and vortex generators were performed with flow visualization as well as force and moment measurements. Test results showed that the origin of the lift dump was caused by the secondary boundary layer flow separation generated from the strong interaction between wing and flap. Various solutions for avoiding the unfavorable feature were suggested with the merits and demerits.

• 대한기계학회논문집B
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• 제28권12호
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• pp.1511-1520
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• 2004

A flow visualization of the two-dimensional rigid fling-clap motions of the flat-plate wing are performed to gain knowledge of butterfly mechanisms that might be employed by butterflies during flight. In this numerical visualization, the time-dependent Navier-Stokes equations are solved for cyclic fling and clap types of wing motion. The separation vortex pair that is developed in the fling phase of the cyclic fling and clap motion is observed to be stronger than those of the fling followed by clap and pause motion(1st cycle motion). This stronger separation vortex pair in the fling phase is attributable to the separation vortex pair of the outside space developed in the clap phase as it moves into the opening in the following fling phase. Accordingly, higher lift and power expenditure coefficients in the fling after clap phase is caused by the stronger separation vortex pair.