• 항공우주시스템공학회지
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• 제3권1호
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• pp.42-46
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• 2009

The 1st development of "Human Powered Aircraft(HPA)" in Korea has been conducting by KAFA(Korea Air Force Academy) from Aug. 2008 to now. HPA is an aircraft powered by directly human energy. The thrust provided by the human power may be the only source and that is weak. Therefore, light weight and strong structure is first requirement. In this paper, treating a basic conceptual design of HPA and material property and material choice for HPA. Also analysing the structure and checking the safety of HPA.

• International Journal of Naval Architecture and Ocean Engineering
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• 제11권1호
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• pp.131-142
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• 2019

In this paper, a Wavy Twisted Rudder (WTR) is proposed to address the discontinuity of the twisted section and increase the stalling angle in comparison to a conventional full-spade Twisted Rudder (TR). The wave configuration was applied to a KRISO Container Ship (KCS) to confirm the characteristics of the rudder under the influence of the propeller wake. The resistance, self-propulsion performance, and rudder force at high angles of the wavy twisted rudder and twisted rudder were compared using Computational Fluid Dynamics (CFD). The numerical results were compared with the experimental results. The WTR differed from the TR in the degree of separation flow at large rudder angles. This was verified by visualizing the streamline around the rudder. The results confirmed the superiority of the WTR in terms of its delayed stall and high lift-drag ratio.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2008년도 Techno-Fair 및 추계학술대회 논문집 전기물성,응용부문
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• pp.175-176
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• 2008

An ultrasonic motor of high torque with a new configuration for application in automobiles is proposed. The newly designed stator is two sided vibrator consisting of a toothed metal disk with a piezoelectric ceramic ring bonded on both faces of the disk which generates a flexural traveling wave along the circumference of disk. In this configuration, the displacement on the surface of stator may not be confined. It also produces a large vibrating force and amplitude because the vibrator is sandwiched by two piezoelectric plates. It is possible to increase the torque by improving the vibration characteristics. To compute the vibration mode of the motor of diameter 48 mm, the finite element method was used. A 6th mode was chosen as the operation mode with a resonance frequency of about 64.4 kHz. According to this design and measured its performance, a prototype was fabricated. The performance measurement of the prototype motor showed that its stall torque was about 1.8 Nm and efficiency was 37 % at 60 % of the maximum torque.

• International Journal of Aeronautical and Space Sciences
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• 제10권2호
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• pp.23-33
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• 2009

The inherent aeromechanical complexity of a rotor system necessitated the comprehensive analysis code for helicopter rotor system. In the present study, an aerodynamic analysis module has been developed as a part of rotorcraft comprehensive program. Aerodynamic analysis module is largely classified into airload calculation routine and inflow analysis routine. For airload calculation, quasi-steady analysis model is employed based on the blade element method with the correction of unsteady aerodynamic effects. In order to take unsteady effects - body motion effects and dynamic stall - into account, aerodynamic coefficients are corrected by considering Leishman-Beddoes's unsteady model. Various inflow models and vortex wake models are implemented in the aerodynamic module to consider wake induced inflow. Specifically, linear inflow, dynamic inflow, prescribed wake and free wake model are integrated into the present module. The aerodynamic characteristics of each method are compared and validated against available experimental data such as Elliot's induced inflow distribution and sectional normal force coefficients of AH-1G. In order to validate unsteady aerodynamic model, 2-D unsteady model for NACA0012 airfoil is validated against aerodynamic coefficients of McAlister's experimental data.

• 항공우주기술
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• 제8권1호
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• pp.197-206
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• 2009

스마트 무인기의 공력특성을 향상시키기 위하여 주익에는 와류생성기(vortex generator), 주익의 끝단에는 유동펜스(flow fence)를 적용하였다. 와류생성기는 SUAV의 최대양력계수와 실속각을 지연시키는 효과가 있었지만 높은 항력증가를 초래하여, 결국에는 양항비가 줄어들었다. 이를 개선하기 위하여 L-형태와 높이가 3mm와 5mm인 와류생성기를 적용하였다. 유동펜스는 나셀 틸팅각이 증가함에 따라 나셀에서 발생하는 박리에 의하여 주익성능이 감소하는 현상을 방지하기 위하여 사용하였다. 두 가지 유동제어 장치를 사용함에 따라 스마트 무인기의 공력특성들이 어떻게 변화하였는지를 정리하였다.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2008년도 추계학술대회 논문집 Vol.21
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• pp.187-188
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• 2008

An ultrasonic motor of high torque with a new configuration for application in automobiles is proposed. The newly designed stator is a two sided vibrator consisting of a toothed metal disk with a piezoelectric ceramic ring bonded on both faces of the disk which generates a flexural traveling wave along the circumference of disk. In this configuration, the displacement on the surface of stator may not be confined. It also produces a large vibrating force and amplitude because the vibrator is sandwiched by two piezoelectric plates. It is possible to increase the torque by improving the vibration characteristics. To compute the vibration mode of the motor of diameter 48 mm, the finite element method was used. A 6th mode was chosen as the operation mode with a resonance frequency of about 64.4 kHz. According to this design and measured its performance, a prototype was fabricated. The performance measurement of the prototype motor showed that its stall torque was about 1.8 Nm and efficiency was 37% at 60% of the maximum torque.

• 한국전산유체공학회지
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• 제21권3호
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• pp.48-54
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• 2016

In the present work, numerical simulations were conducted on the scaled model of the BWB type UCAV in the subsonic region using ANSYS FLUENT V15. The prediction method was validated through comparison with experimental results and the effect of the twisted wing was investigated. To consider the transitional flow phenomenon, ${\gamma}$ transition model based on SST model was adopted. The coefficients of lift, drag and pitching moment were compared with experimental results and the pressure distribution and streamlines were investigated. The twisted wing decreases the lift force but increases lift-to-drag ratio through delay of stall and leading edge vortex's movement to the front, also the non-linearity of the pitching moment is decreased.

• 한국유체기계학회 논문집
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• 제18권6호
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• pp.63-70
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• 2015

This paper proposes a novel airfoil named "KA2" for the blade of the wind turbine systems. Dynamic loads characteristics are analyzed and compared using aerodynamic data of ten airfoils including the proposed airfoil. The blade is divided into the sixteen elements in the longitudinal direction of the blade for applying the Blade Element Method Theory (BEMT) method, and in each element, torque, thrust, and pitching moment are calculated using turbulent time varying wind speed and aerodynamic data of each wing. Additionally, each force and torque is accumulated in the whole region of the blade for the estimation of representative values. The magnitude of such forces is comparatively analyzed for different airfoils. The angle of attack is constant below the rated wind speed due to the fact that the tip speed ratio is kept at the constant value, and it increases in the region of over rated wind speed as the tip speed ratio decreasing with constant rated rpm and increasing wind speed. Such increase in the angle of attack causes the changes of the force acting on the airfoil with different characteristics of lift and drag in the stall region of each different airfoil. Even though the mean wind speed is in the rated speed in a given time, because of the turbulence, it has either the over rated or under rated speed most of the time. Furthermore, the dynamic properties of each force are analyzed in this rated wind speed in order to objectively understand the dynamic properties of the blades which are designed based on the different airfoils. These dynamic properties are also compared by the standard deviation of time varying characteristics. Moreover, the output characteristics of the wind turbine are investigated with different airfoils and wind speeds. Based on these investigations, it was revealed that the proposed airfoil (KA2) is well applicable to the blade with passive pitch control system.

• 한국항공우주학회지
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• 제35권12호
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• pp.1059-1066
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• 2007

타원형 단면 에어포일의 블로잉 제트에 의한 유동박리 제어효과에 대한 연구를 레이놀즈수 Rec=7.84×105에서 실험적 방법으로 수행하였다. 블로잉 제트는 에어포일 내부의 공기실에 있는 압축공기를 앞전 혹은 뒷전에 위치한 좁은 제트슬롯을 통하여 분출시켰다. 실험결과 블로잉은 날개면 압력회복으로 수직력을 증가시킴으로써 박리 유동을 제어할 수 있음을 보였다. 블로잉에 의한 수직력의 상승은 상대적으로 높은 받음각에서 더욱 효과가 컸으며 낮은 받음각에서는 감소되었다. 현 연구조건에서 수직력을 상승시키는데 가장 효과적인 블로잉 방식은 앞전에서의 90° 방향의 간헐제트이었다. 특히, 간헐제트가 부여된 경우 실속 받음각을 약 2°-3° 지연시킬 수 있었다. 연속제트와 간헐제트 모두 에어포일의 공력특성과 성능을 향상시킴으로써 유동박리 제어에 직접적이고 유효한 방법임을 입증하였다.

• 대한조선학회지
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• 제27권4호
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• pp.27-31
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• 1990

양력면(揚力面)의 양력계산(揚力計算)에 흔히 쓰이고 있는 방법(方法)을 크게 나누면 Vortex Lattice 법(法)과 Mode Function법(法)이 있다. 잘 알려진 것 처럼, Vortex Lattice법(法)은 해(解)의 수렴성(收斂性)은 좋으나 계산시간(計算時間)이 많이 걸리는 문제점(問題點)이 있고, Mode Function법(法)은 계산시간(計算時間)은 짧으나 해(解)가 특이(特異)해 지는 경우가 있다. 그러므로 본(本) 논문(論文)에서는 양방법(兩方法)의 장점(長點)들을 살리도록, 양력면(揚力面)을 Span 방향(方向)으로 분할(分割)하고 각(各) Strip Mode Function을 사용하여 Vortex를 분포(分布)시켜, 양력면이론(揚力面理論)으로 양력(揚力)을 계산(計算)하였다. 우선 Horn Type의 반균형타(半均衡舵)에 본(本) 계산법(計算法)을 적용(適用)하여 타직압력(舵直壓力)을 계산(計算)하고 타(舵) 단독시험(單獨試驗)을 병행(竝行)하여 계산법(計算法)의 유용성(有用性)을 검증(檢證)하였다. 그 결과(結果), Stall과 같은 비선형적(非線形的) 유체현상(流體現象)이 일어나지 않는 한(限), 본(本) 계산법(計算法)은 유용(有用)하다는 결론(結論)을 얻었다. 끝으로, 본(本) 계산법(計算法)을 평행(平行)하게 늘어선 한척(隻)의 장방형타(長方形舵)에 적용(適用)하여 두 타(舵) 사이의 상호간섭(相互干涉)도 계산(計算)하였다.