• 대한조선학회논문집
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• 제50권5호
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• pp.343-348
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• 2013

When a natural frequency of the trailing edge of a wing is close to a vortex shedding frequency, an amplitude of the edge oscillation becomes maximal; it makes intensive noise called singing. Motion of the trailing edge may also feedback to the vortex shedding so that self-sustained oscillation appears, and a resonant frequency is locked in some interval of the speed of the incident flow. In this study, we first evaluate main features of oscillating characteristics of the wing. Second we simulate fluid-structure interaction of the wing with a flap using a commercial code, ANSYS-CFX, and investigate lift characteristics in a frequency domain.

• 한국가시화정보학회지
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• 제3권2호
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• pp.63-70
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• 2005

Birds and insects flap their wings to fly in the air and they can change their wing motions to do steering and maneuvering. Therefore, we created various wing motions with the parameters which affected flapping motion and evaluated the aerodynamic characteristics about those cases in this study. As the wing rotational velocity was fast and the rotational timing was advanced, the measured aerodynamic forces showed drastic increase near the end of stroke. The mean lift coefficient was increased until angle of attack of $50^{\circ}$ and showed the maximum value of 1.0. The maximum mean lift to drag ratio took place at angle of attack of $20^{\circ}$. Flow fields were also visualized around the wing using particle image velocimetry (PIV). From the flow visualization, leading-edge vortex was not shed at mid-stroke until angle of attack of $50^{\circ}$. But it was begun to shed at angle of attack of $60^{\circ}$.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2001년도 춘계학술대회 논문집
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• pp.719-722
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• 2001

Paraglider has been used for a good air sports instrument by many people in the world though its short history. And manufacturers have improved it continuously. It has the great growth from the first model like parachute to the latest model that has the extreme speed, but we can improve it in more parts. In this paper, we will show the method which can improve its performance by using Axiomatic Approach.

• 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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• 제28권7호
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• pp.800-808
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• 2004

Wind tunnel test of an airplane model with forward swept wing was done in KARI LSWT to evaluate and measure the aerodynamic characteristics of initially designed configuration. Since the given wing planform did not fully satisfy the design requirements, local flow control devices such as vortilon, vortex generator and flow fence were used to delay separation and to enhance aerodynamic characteristics. Also decision making processes of design parameters such as vertical tail boom length, the location, size and the incidence angle of horizontal tail were discussed. The general aerodynamic characteristics of forward swept wing for various control surface deflection conditions of flap, aileron and elevator were also given.

• 한국철도학회논문집
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• 제10권6호
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• pp.786-791
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• 2007

고속열차의 속도가 300km/h 이상이 되면 난류의 박리나 와류발산 등에 의한 공력소음의 영향이 지배적이 된다. 본 연구에서는 KTX와 한국형고속열차의 외부에서 발생하는 공력소음, 특히 차간 공간에서 발생하는 소음의 특성을 시험을 통해 규명한다. 차량 실내외의 소음 측정을 통해 이 소음의 특성을 분석하였고, 풍동시험을 통해 머드플랩 사이의 틈의 크기가 저주파 소음 발생에 직접적인 영향을 준다는 것을 규명하였다. 또한 마이크로폰어에이 시험으로 고속열차의 외부에서 발생하는 소음의 주파수 특성을 분석하였다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.209-212
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• 2006

Insect and birds in nature flap their wings to generate fluid dynamic forces that are required for the locomotion. Most of the previous published papers discussed mainly on the effect of flapping parameters such as flapping frequency and amplitude on the thrust at a fixed Reynolds number. However, it is not much known on the values of the flapping parameters that the flapping wing requires to generate the thrust at the low Reynolds number flow. In this paper, the onset of the thrust generation is investigated using the lattice Boltzmann method. The wake patterns and velocity profiles behind a flat plate in heaving oscillation are investigated for the heaving amplitude of 0.5C. The time-averaged thrust coefficient value is investigated by changing the reduced frequency from 0.125 to 3.0 for three values of heaving amplitude (h/C=0.25, 0.325, 0.50). It is also found that the critical Strouhal number over which the flat plate starts to produce the thrust is around 0.1 and the thrust is an exponential function of the Strouhal number.

• International Journal of Naval Architecture and Ocean Engineering
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• 제9권1호
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• pp.55-65
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• 2017

Underwater torpedo has control fin with very low aspect ratio due to launching from limited size of cylindrical torpedo tube. If the aspect ratio of control fin of underwater vehicle is very low three-dimensional flow around control fin largely reduces control forces. In this study, the end plate was applied to reduce the three-dimensional flow effects of partially movable control fin of underwater vehicle. Through numerical simulations the flow field around control fin was examined with and without end plate for different flap angles. The pressure, vorticity, lift and torque on the control fin were analyzed and compared to experiments. The comparison have shown a reasonable agreement between numerical and experimental results and the effect of end plate on a low aspect ratio control fin. When the end plate was attached to the movable control fin, the lift increased and the actuator shaft torque did not significantly change. As this means less consumption of the actuator shaft torque compared to the control fin that has the same control force, the inner actuator capacity can be reduced and energy consumption can be saved. Considering this, it is expected to be effectively applied to the control fin design of underwater vehicles such as torpedoes.

• 한국항공우주학회지
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• 제35권5호
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• pp.397-403
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• 2007

자연에 존재하는 곤충과 새들은 날개짓을 통하여 이동에 필요한 유체력을 발생시킨다. 실현 가능한 플랩핑 MAV를 개발하기 위해서는 날개짓과 추력발생사이의 관계에 관한 기초연구가 필요하다. 본 연구에서는 격자볼츠만법을 사용하여 히빙진동 운동을 하는 평판날개에서 추력 발생이 시작되는 조건을 파악하고자 하였다. 히빙진폭을 0.5C로 고정시키고 환원주파수가 추력발생에 미치는 영향을 파악하였다. 다양한 경우의 히빙진폭에 대하여 환원주파수와 추력 사이의 관계를 파악하고, 추력발생에 더 중요한 파라메터가 Strouhal수임을 보였다. Reynolds수 변화에 따른 추력특성을 파악하였다. 본 연구결과 추력발생이 시작되는 임계 Strouhal 수는 약 0.12이며 추력은 Strouhal 수에 대하여 지수함수의 관계를 갖는다.