• International Journal of Aeronautical and Space Sciences
• /
• 제3권2호
• /
• pp.82-87
• /
• 2002

Aerodynamic analysis of NACA wings moving with a constant speed over guideways are performed using an indirect boundary element method (potential-based panel method). An integral equation is obtained by applying Green's theorem on all surfaces of the fluid domain. The surfaces over the wing and the guideways are discretized as rectangular panel elements. Constant strength singularities are distributed over the panel elements. The viscous shear layer behind the wing is represented by constant strength dipoles. The unknown strengths of potentials are determined by inverting the aerodynamic influence coefficient matrices constructed by using the no penetration conditions on the surfaces and the Kutta condition at the trailing edge of the wing. The aerodynamic characteristics for the wings flying over nonplanar ground surfaces are investigated for several ground heights.

• 한국군사과학기술학회지
• /
• 제9권4호
• /
• pp.104-113
• /
• 2006

To identify aeroelastic characteristics of wings with double-folding mechanism, aeroelastic analyses are performed. There are four wing models which consist of one linear model and three nonlinear models. The nonlinear models have one or two freeplay nonlinearties. The describing function method is used to approximately examine nonlinear effects. The aeroelastic module in MSC/NASTRAN is used to study the aeroelastic characteristics of the considered wing models. The effects of the folding mechanism and amplitude ratio are examined. As the amplitude ratio increases, the flutter speeds approach to those of the wing model with only one nonlinearity. The numerical results show that the flutter speeds of the wings with double-folding mechanism can be lower or higher than those of the wing model with only one folding mechanism depending upon the direction of the second folding mechanism.

• 한국생산제조학회지
• /
• 제20권5호
• /
• pp.605-611
• /
• 2011

In this study, based on previous studies, the thrust generated by using flapping tandem wings is examined. We studied on the relationship between the parameters for characterizing oscillatory tandem wings (namely, the Strouhal number and Reynolds number) for thrust generation in micro flow regime. At each Reynolds number, Strouhal number, heaving amplitude, distance between tandem wings, and phase difference are varied and the flapping motions of tandem mode are calculated to find the optimum conditions for generating thrust. As a result, comparing with a single flapping mode, we found that the minimum Strouhal number for generating thrust is shifted down up to approximately 25% when the tandem flapping mode is applied.

• 천문학회지
• /
• 제39권2호
• /
• pp.31-40
• /
• 2006

Near-IR $H_2$ emission features in the northern region of the Orion A giant molecular cloud were observed in the $CO\;J\;=\;1\;{\rightarrow}\;0$ line in search of CO outflows. Out of the 30 sources surveyed, CO line wings were detected toward 28 positions, suggesting a strong correlation between $H_2$ jets and CO outflows. Blueshifted wings were detected toward 26 positions while redshifted wings were detected toward 15 positions, which suggests that there is a bias in the source selection. The bias is more severe in OMC 3 than in OMC 2. Since the protostars in OMC 3 are younger and more deeply embedded, the bias may be caused by the difference of extinction between blueshifted and redshifted outflows. Some physical parameters of the outflows were derived from the line profiles.

• 한국컴퓨터정보학회:학술대회논문집
• /
• 한국컴퓨터정보학회 2014년도 제49차 동계학술대회논문집 22권1호
• /
• pp.81-82
• /
• 2014

본 논문에서는 Windows Phone 기반의 모바일 게임 Wings를 설계하고 구현한다. 이 게임은 랜덤하게 다양한 비행체 캐릭터가 적기로 출현하도록 구현하고, 플레이어는 터치한 방향으로 이동하면서 미사일을 오토샷으로 발사하도록 구현한다. 적기를 파괴하여 획득한 점수는 격리된 저장소 영역을 이용하여 Windows phone내에 생성하여 저장하도록 구현한다. 이 게임은 C# 언어를 사용하여 구현하였기 때문에 메모리 누수 및 생산성에 대한 부담을 덜 수 있다. Wings 게임은 Windows 용 앱 스토어인 마켓플레이스에 등록하여 다운로드 가능하게 할 것이다.

• International Journal of Aerospace System Engineering
• /
• 제10권1호
• /
• pp.1-13
• /
• 2023

The present study was attempted to investigate flow interference effects and the aerodynamic characteristics of the front and rear wings of a joined-wing aircraft by changing the configuration variables. The study was performed using a computational fluid dynamics(CFD) tool to demonstrate forward flight and analyze aerodynamic characteristics. A total of 9 configurations were analyzed with variations on the position, height, dihedral angle, incidence angle, twist angle, sweepback angle, and wing area ratio of the front and rear wings while the fuselage was fixed. The quantities of aerodynamic coefficients were confirmed in accordance with joined-wing configurations. The closer the front and rear wings were located, the greater the flow interference effects tended. Interestingly, the rear wing did not any configuration change, the lift coefficient of the rear wing was decreased when adjusted to increase the incidence angle of the front wing. The phenomenon was appeared due to an effective angle of attack alteration of the rear wing resulting from the flow interference by the front wing configurations.

• 항공우주시스템공학회지
• /
• 제3권2호
• /
• pp.1-11
• /
• 2009

A structural modelling for study on dynamic characteristics of tapered composite aircraft wings in the form of thin-walled beam is presented. The proposed structural model includes effects of transverse shear flexibility exhibited by the advanced composite materials and warping restraint characterizing elastic anisotropy and induced structural couplings. The complex effects of these factors could have a role in more efficient analysis on those structural models.

• Journal of Mechanical Science and Technology
• /
• 제15권11호
• /
• pp.1548-1554
• /
• 2001

Flow patterns and dynamic properties of two-stage Weis-Fogh type ship propulsion mechanism are studied by a discrete vortex method. To study mutual interference between two wings, two cases are con sidered - wing motions with the same and reverse phases. The predicted flow patterns correspond to the available flow visualization results. Time histories of thrust and drag coefficients are also calculated, and the interference between the two wings are numerically clarified.

• 대한토목학회논문집
• /
• 제14권3호
• /
• pp.429-438
• /
• 1994

3차원 유한요소 모델을 사용하여 여러 wing들로 구성된 3차원 다중 구조물의 해석을 수행할 경우에는 입력자료 작성시 번거로움과 긴 해석시간 및 큰 용량의 컴퓨터가 필요하게 된다. 본 연구에서는 이런 문제점을 효율적으로 극복할 수 있는 여러 wing들로 구성된 3차원 구조물에 대한 해석모델들을 제안하였으며 이들 해석모델에는 3차원 다중 구조물에서 계산의 간편성 때문에 통상 무시되어 온 바닥슬라브의 면내변형이 고려되어져 있다. 본 연구에서 제안하는 해석모델에서는 여러 wing들로 구성된 3차원 구조물을 하나의 구조물로 취급하는 종래의 방법 대신에 각 wing 구조물들과 이들 wing 구조물을 서로 연결시켜주는 연결부로 이상화하기 때문에 다양한 형태(Y. U, H 등)의 구조물에도 쉽게 적용할 수 있다. 제안된 해석모델의 정확성은 두가지 구조방식의 예제 구조물에 대하여 3차원 유한 요소 모델과 제안된 해석모델로부터 구한 해석결과(구조물의 고유 진동주기, 모드형상, 임의 절점에서의 변위에 대한 시간이력)의 비교로부터 검증되었으며 그 결과 제안된 해석모델은 여러 wing들로 구성된 3차원 구조물에 대한 근사적인 모델로 적합함을 알 수 있었다.

• 대한조선학회논문집
• /
• 제48권5호
• /
• pp.381-389
• /
• 2011

In this study, we are focusing our attention on lift characteristics of the low aspect wings for Wing-In Ground effect crafts (WIG). Experimental measurements at an open-type wind tunnel are carried out and results are comparatively presented. In order to simulate the realistic ground condition in where the WIG craft is flying, moving ground is implemented by a conveyor belt rotating with the same velocity of the inflow. We consider two different wings (NACA0012 and DHMTU section) which have four different aspect ratios (0.5, 1.0, 1.5 and 2.0). Forces acting on the wings are measured and lift characteristics are elaborately investigated for various different conditions. In addition, end-plate effects are estimated. Results are validated by comparing with theoretic solutions of the symmetric airfoil. Present results show that ground effects are differently generated in moving or fixed ground conditions, and hence left characteristics are affected by the ground condition. Consequently, accurate aerodynamic forces acting on the WIG craft are guaranteed in a realistic moving ground condition.