• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회A
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• pp.395-398
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• 2007

In nature, the swallowtail butterfly is known to be a versatile flyer using gliding and flapping efficiently. Furthermore, it has long tails on the hind-wing that may be associated with the enhancement of the gliding performance. In the present study, we investigate the aerodynamic property of swallowtail butterfly wing in gliding. We use an immersed boundary method and conduct a numerical simulation at the Reynolds numbers of 1,000 - 3,000 based on the free-stream velocity and the averaged chord length for seven different attack angles. As a result, we clearly identify the existence of the wing-tip and leading-edge vortices, and a pair of the streamwise vortices generated along the hind-wing tails. Interestingly, at the attack angle of $10^{\circ},$ hairpin vortices are generated above the center of the body and travel downstream.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.1-7
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• 2016

During flight of the aircraft, the vortex merging phenomenon appears under the certain condition between co-rotating vortices which were generated at the wing tip and lifting-surface. And then these merged vortices at both sides show counter-rotating pattern to affect on the downstream of the aircraft. In this paper, the numerical simulations are conducted assuming this phenomenon in two-dimensional co-rotating or counter-rotating vortices pairs. Two-dimensional incompressible Navier-Stokes equations were converted into Vorticity-Streamfunction form and the Galerkin spectral method was adopted. The third order Runge-Kutta method was used for time integration. The effects on the vortex merger and degree of vortex merger were investigated according to time, Reynolds number, and changes in the distance between two vortices.

• Journal of Mechanical Science and Technology
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• 제19권2호
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• pp.674-681
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• 2005

The unsteady evolution of trailing vortex sheets behind wings in close formation flight near the ground is simulated using a discrete vortex method. The ground effect is included by an image method. The method is validated by comparing computed results with other numerical results. For a lifting line with an elliptic loading, the ground has an effect of moving wingtip vortices laterally outward and suppressing the development of vortex evolution. The gap between wings in close formation flight has an effect of moving up wingtip vortices facing each other. For wings flying in parallel, the ground effect causes the wingtip vortices facing each other to move up, and it makes the opposite wing tip vortices to move laterally outward. When there is a relative height between the wings in ground effect, right-hand side wingtip vortices from a mothership move laterally inward.

• 한국항공우주학회지
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• 제44권12호
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• pp.1017-1026
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• 2016

두 가지의 비표면 가시화 기법과 이들 기법의 와류 적용 예를 기술한다. 두 가지 가시화 기법 중 하나는 전통적인 연기선 기법이고, 또 다른 하나는 가정용 초음파 가습기에서 발생하는 미세 수적을 사용하는 기법이다. 연기선 기법은 공기 흐름 속도에 제한이 있으며(0.07 mm 지름의 연기선의 경우 약 5 m/sec), 오염의 문제점이 있지만 매우 정교하고 선명한 연기 유맥선 시트를 발생시킬 수 있다. 이 기법은 3차원 날개의 날개 끝 와류의 가시화에 적용되었다. 초음파 가습기 미세 수적 기법은 연기선 기법에 비하여 공기 흐름 속도를 보다 크게 할 수 있으며(10 m/sec 이상), 독성과 오염의 문제를 해결할 수 있다. 초음파 가습기 미세 수적 기법은 정점 스트레이크를 가지는 이중 삼각날개에서 발생하는 복잡한 와류 시스템의 가시화에 성공적으로 적용되었다.

• Advances in aircraft and spacecraft science
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• 제10권2호
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• pp.107-125
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• 2023

Drag reduction is significant research in aircraft design due to its effect on the cost of operation and carbon footprint reduction. Aircraft currently use conventional solid winglets to reduce the induced drag, adding extra structural weight. Fluidic on-demand winglets can effectively reduce drag for low-speed flight regimes without adding any extra weight. These utilize the spanwise airflow from the wingtips using hydraulic actuators to create jets that negate tip vortices. This study develops a computational model to investigate fluidic on-demand winglets. The well-validated computational model is applied to investigate the effect of injection velocity and angle on the aerodynamic coefficients of a rectangular wing. Further, the turbulence parameters such as turbulent kinetic energy (TKE) and turbulent dissipation rate are studied in detail at various velocity injections and at an angle of 30°. The results show that the increase in injection velocity shifted the vortex core away from the wing tip and the increase in injection angle shifted the vortex core in the vertical direction. Further, it was found that a 30° injection is efficient among all injection velocities and highly efficient at a velocity ratio of 3. This technology can be adopted in any aircraft, effectively working at various angles of attack. The culmination of this study is that the implementation of fluidic winglets leads to a significant reduction in drag at low speeds for low aspect ratio wings.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2012년도 추계학술대회 논문집
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• pp.71-74
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• 2012

Generally, tone noise is generated at the rotary wing and helicopter. BVI(Blade-Vortex Interaction) noise is one of the helicopter's tone noise. The BVI noise is governed by tip-vortex characteristics such as vortex size, strength and trajectory. To avoid BVI, many methods have been developed and proposed. In this paper, rotating blade with active tab was numerically investigated to reduce BVI noise. For flow and noise simulation, the lifting surface approach and the acoustic analogy were used. Using numerical methods, the noise directivity and maximum noise position were predicted.

• 한국항공우주학회지
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• 제30권4호
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• pp.10-17
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• 2002

간접 경계요소법 (비정상패널법)을 사용하여 3차원 날개의 동적 지면효과에 대한 연구를 수행하였다. Green 정리를 사용하여 경계표면에 대한 적분방정식을 얻었다. 일정강도의 용출 및 용흡중첩을 날개표면에 분포시켰고 후류는 일정강도의 용흡중첩으로 나타내었다. 매 시간간격마다 한 행의 후류 패널들이 날개의 후연에서 하류로 대류한다고 가정하였다. 지면효과를 받는 날개의 익단 와류가 날개길이방향으로 이동하였다. 동적 지면효과를 받는 날개가 가지는 공력계수의 진폭 값이 정적 지면효과를 받는 날개의 경우보다 더욱 증가하였다.

• 해양환경안전학회지
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• 제25권6호
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• pp.757-764
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• 2019

수중에서 빠른 속도로 운동하는 물체 주변에서 감압이 발생하며, 이로 인해 공동 핵이 팽창함으로써 캐비테이션이 발생한다. 캐비테이션이 발생하게 되면 소음 및 진동이 증가하며, 추진기의 경우 추진 성능이 저해되는 악영향을 초래하기 때문에 이에 대한 예측이 필요하다. 본 연구에서는, 캐비테이션 발생으로 인한 공동소음의 해석절차를 정립하고, 타원형 날개에 적용하였다. 먼저 전산유체역학해석을 수행하여, 날개 형상 주위 유동장 정보를 도출하였다. 공동 핵 밀도 함수를 활용하여, 핵의 초기 반경 별로 개수를 계산하였고 이들을 압력 강하가 큰 날개 끝 전류에 랜덤하게 배치하였다. 이후 공동소음 해석을 위해 각각의 핵에 대하여 Lagrangian 관점에서 버블 다이나믹스를 활용하였고, 계산된 공동의 거동으로부터 소음해석을 수행하였다. 공동소음은 광대역 소음의 특성을 가지는 것을 확인하였으며, 최종적으로 선박해양플랜트연구소(KRISO)의 대형캐비테이션터널(LCT)에서 수행된 실험 계측결과와의 비교를 통해 검증을 수행하였다.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2009년도 추계학술대회 논문집
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• pp.473-473
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• 2009

There have been many academic researches on the aerodynamic design of wind turbine based on blade element method (BEM) and momentum theory (MT, or actuating disk theory). However, in the real world, the turbine blade design requires many additional constraints more than theoretical analysis. The standard procedure is studied in the present paper to design new blades for the wind turbine system ranged from the small size from 1 to 10 kW. From the experience of full design of a 10 kW blade, the authors tried to set up a standard procedure for the aerodynamic design based on IEC 61400-2. Wind-turbine scale, rotating speed, and geometrical chord/twist distribution at the segmented span positions are calculated with a suitable BEM/MT code, and the geometrical shape of tip and root should be modified after considering various parameters: wing-tip vortex, aerodynamic noise, turbine efficiency, structural safety, convenience of fabrication, and even economic factor likes price, etc. The evaluated data is passed to the next procedure of structural design, but some of them should still be corresponded with each other: the fluid-structure interaction is one of those problems not yet solved, for example. Consequently, the design procedure of small wind-turbine blades is set up for the mass production of commercial products in this research.

• 한국항공운항학회지
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• 제24권2호
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• pp.19-24
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• 2016

Positional stability analysis based on aerodynamic forces and induced moments of formation flight using two small aircraft models is presented. The aerodynamic force and moments of the trailing aircraft are analyzed in the aspect of flight stability. The induced moments with the change of local flow direction by wing-tip vortex from the leading aircraft can affect the flight positional stability of aircraft in closed formation flight. Aerodynamic forces and moments of trailing aircraft model are measured by 6-component internal balance at the 49 locations with vertical and lateral space between two aircraft models. Results are shown that the positional stability of trailing aircraft in formation flight can be analyzed by positional stability derivatives with vertical and lateral space. It is concluded that flying positions can be important factors for aircraft position stability due to induced aerodynamic force and moments with vertical and lateral spacing by the variation of flow pattern from the leading aircraft in formation flight.