• 한국수자원학회:학술대회논문집
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• 한국수자원학회 2008년도 학술발표회 논문집
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• pp.2141-2145
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• 2008

저면에 힌지로 연결된 3종류의 부유 플랩 시스템을 대상으로 수리모형실험을 실시하였다. 이 시스템은 입사파를 반사시키고, 구조적 감쇄 및 점성 감쇄를 이용하여 파랑에너지를 감소시켜 차폐 해역을 제공한다. 다양한 파랑조건에 대하여 파랑의 반사, 전달, 플랩의 회전각 등을 분석하였다. 외해 날개벽을 부착한 형태가 파랑의 전달을 최소화시킬 수 있다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 추계학술대회논문집B
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• pp.615-620
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• 2000

Manoeuvrability of ships has been receiving a great deal of attention both concerning navigation safety and the prediction of ship manoeuvring characteristics, especially at the preliminary design stage. Recently, in order to improve manoeuvrability of ships, High-lift devices could be applied to design of rudder at design stage. Now, among the them, we carried out the flow visualization and investigation of flow field around a flapped rudder(trailing-edge flap). A trailing-edge flap is simply a portion of the trailing-edge section of airfoil that is hinged and which can be deflected upward or downward. Flow visualization results of flap defection shown as follow Photos including main body and flap defection.

• 수산해양기술연구
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• 제56권2호
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• pp.172-182
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• 2020

In order to offer specific information needed to assist in operation of a ship with same type rudder through evaluating the maneuverability of training ship A-Ra with flapped rudder, sea trials based full scale for turning test, zig-zag test with rudder angle 10° and 20°, and spiral test at service condition were carried out on starboard and port sides around Jeju Island according to the standards of maneuverability of IMO. As a result, the angular velocity of port turn was higher than that of starboard turn. Therefore, the size of turning circle was longer on the starboard side. In addition, variation of the transfer due to various factors was more stable than those of the others. In the Z-test results, the mean of 1st and 2nd overshoot angles were 9.8°, 6.3° and 15.3°, 9.2° respectively when the port and starboard was 10°; the 1st overshoot angle were 18°, 13.7° when using 20°. Her maneuverability index T' and K' can be easily determined by using a computer with the data obtained from Z-test where K' and T' are dimensionless constants representing turning ability and responsiveness to the helm, respectively. In the Z-test under flap rudder angle 10°, the obtained K' value covered the range of 2.37-2.87 and T' was 1.74-3.45. Under the flap rudder angle 20°, K' and T' value showed 1.43-1.63, 1.0-1.73, respectively. In the spiral test, the loop width was unstable at +0.3° and -0.5°-0.9° around the midship of flap rudder. As a result, course stability was comparatively good. From the sea trial results, training ship ARA met the present criterion in the standards of maneuverability of IMO.

• 한국전산유체공학회지
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• 제18권3호
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• pp.42-50
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• 2013

The supersonic airplane with flapped biplane, Busemann biplane equipped flap, is superior to drag and noise reduction due to wave cancelation effect between upper and lower airfoils. In this study, it is numerically calculated and analyzed the lift, drag and lift to drag ratio of flapped biplane with respect to various the length and angle of the flap. Euler solver of EDISON CFD, web based computational fluid dynamic solver for the purpose of education, is employed. Depending on the length of the flap, lift and drag increase linearly, and there exists the optimum flap angle which maximize the lift-to-drag ratio at the freestream mach 2.0 on-design condition. The predictable relational expression is driven as liner equation. As a results of comparison with drag of flapped biplane, Busemann biplane, and diamond airfoil with the same lift, the drag of flapped biplane is 88.76% lower than that of the Busemann biplane and 70.67% lower than that of the diamond airfoil. In addition, the change of pressure is compared to confirm the noise reduction effect of flapped biplane at h/c=5 of lower airfoil. The shock strength of flapped biplane is smaller than that of other airfoils.

• Advances in aircraft and spacecraft science
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• 제2권3호
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• pp.329-343
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• 2015

This study aimed to observe the effect of a novel concept (referred to as the flap extension) implemented on the leading edge of the flap of a three element high lift device. The high lift device, consisting of a flap, main element and slat is designed around an Airbus research profile for sufficient take off and landing performance of a large commercial aircraft. The concept is realised on the profile and numerically optimised to achieve an optimum geometry. Two different optimisation approaches based on Genetic Algorithm optimisations are used: a zero order approach which makes simplifying assumptions to achieve an optimised solution: as well as a direct approach which employs an optimisation in ANSYS DesignXplorer using RANS calculations. Both methods converge to different optimised solutions due to simplifying assumptions. The solution to the zero order optimisation showed a decreased stall angle and decreased maximum lift coefficient against angle of attack due to early stall onset at the flap. The DesignXplorer optimised solution matched that of the baseline solution very closely. The concept was seen to increase lift locally at the flap for both optimisation methods.

• 한국항공우주학회지
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• 제35권9호
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• pp.761-770
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• 2007

본 연구에서는 압력 왜곡과 유동각 왜곡을 모사하기 위하여 삼각날개를 이용한 와류 발생장치를 설계하였다. 삼각날개는 목표한 와류코어 위치와 압력왜곡율(DC90), 와류각을 만족하기 위해 후퇴각 $65^{\circ}$를 사용하였으며, 와류의 분포 영역을 넓히기 위해 삼각날개 전단면에 $45^{\circ}$ 와동 플랩을 적용하였다. 제작된 와류 발생장치는 시뮬레이션 덕트를 적용한 유동 왜곡 시험에서 전압력 왜곡율의 설계 요구조건을 만족하였으며, 시험 결과로부터 검증된 전산유체해석 결과를 이용하여 와류코어 위치와 와류각의 목표 성능을 확인하였다.

• 한국어업기술학회:학술대회논문집
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• 한국어업기술학회 2005년도 춘계 학술대회 논문집
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• pp.62-69
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• 2005

Maneuverability of ships has been receiving a great deal of attention both concerning navigation safety and the prediction of ship maneuvering characteristics, to improve it. High-lift device could be applied to design of rudder at design stage. Now, we carried out the flow visualization and inversitgation of flow around a flap rudder (trailing-edge flap). Flow visualization results of flap defection shown as the flow around a NACA0020 Flap Rudder will be conducted in a Circulating Water Channel. The purpose of this investigation will be to investigate the development of the separation region on the flap rudder with the variation of angle of attack and determine the angle of attack at which the flow separates and reattaches.

• 대한기계학회논문집 C: 기술과 교육
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• 제2권1호
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• pp.39-46
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• 2014

이 연구에서는 탄성 플랩이 뒷전에 장착된 2차원 날개 단면의 공력 특성을 전산 해석하였다. EDISON_CFD는 날개 주위의 비압축성 난류 유동을 시뮬레이션 하기 위해 이용되었으며, MIDAS_IT는 전산 해석 결과로 얻어진 압력 하중 하에서 탄성 플랩의 변위를 구조해석 하기 위해 사용되었다. EDISON_CFD와 MIDAS_IT의 반복 계산 절차를 이용하여, 플랩의 변위가 수렴되면 해석을 종료하여, 날개 단면에 작용하는 공력을 분석하였다. 양항비의 추정 결과 일정 받음각 이내에서 플랩의 유리한 효과가 나타날 것으로 예상된다.

• Archives of Plastic Surgery
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• 제36권2호
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• pp.147-152
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• 2009

Purpose: First web space contracture of the hand has been treated with various surgical techniques such as Z - plasty, local flap, pedicled flap, distant free flap, and anterolateral thigh free flap. Among those surgical techniques, anterolateral thigh free flap provide a thin and pliable flap, which is a useful method for correction of first web space contracture. Methods: From August 2003 to September 2007, authors selected 9 patients who had first web space contracture with limitation of thumb abduction within 30 degrees. All of patients had received first web contracture release with anterolateral thigh free flap. Age ranged from 24 to 51, and all the patients were male. Average follow up period was 12 months and authors performed photographic analysis of the thumb abduction angle of postoperative increase. Result: All the flaps were survived. Donor site was closed with primary closure in 8 cases and covered with split - thickness skin graft in 1 case. Average flap size was $8{\times}9cm$ and average thickness was 0.6 cm in suprafascial flap. The procedure resulted in increased thumb abduction angle of $34.7^{\circ}$ in average and showed concave shape of first web space in suprafascial flap. Additional operations were performed with Z - plasty in 3 cases, local flap in 5 cases, and opponensplasty in 3 cases. Conclusion: In suprafascial flap, we obtained relatively thin flap thickness and were able to make natural concave shape of first web space. In releasing severe contracture of the first web space, anterolateral thigh free flap provided a good coverage of appropriate thickness and pliable soft tissue and allowed limited donor site morbidity.

• International Journal of Naval Architecture and Ocean Engineering
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• 제1권1호
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• pp.1-12
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• 2009

Wing-in-Ground vehicles and aerodynamically assisted boats take advantage of increased lift and reduced drag of wing sections in the ground proximity. At relatively low speeds or heavy payloads of these craft, a flap at the wing trailing-edge can be applied to boost the aerodynamic lift. The influence of a flap on the two-dimensional NACA 4412 airfoil in viscous ground-effect flow is numerically investigated in this study. The computational method consists of a steady-state, incompressible, finite volume method utilizing the Spalart-Allmaras turbulence model. Grid generation and solution of the Navier-Stokes equations are completed using computer program Fluent. The code is validated against published experimental and numerical results of unbounded flow with a flap, as well as ground-effect motion without a flap. Aerodynamic forces are calculated, and the effects of angle of attack, Reynolds number, ground height, and flap deflection are presented for a split and plain flap. Changes in the flow introduced with the flap addition are also discussed. Overall, the use of a flap on wings with small attack angles is found to be beneficial for small flap deflections up to 5% of the chord, where the contribution of lift augmentation exceeds the drag increase, yielding an augmented lift-to-drag ratio.