• International Journal of Aeronautical and Space Sciences
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• 제15권2호
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• pp.138-145
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• 2014

The initial configuration for 95-seat passenger regional turboprop aircraft, the so called KC950, was designed to meet the market requirements. This paper prescribes the initial design based upon aircraft design guidelines and compared the competitive aircraft configurations after considering the related FAR 25 regulations. More specifically, results of design describe how to select the fuselage cross-sectional area, how to layout the cabin, and how to determine the overall shape and physical dimension of the fuselage. Sizing of wing and empennage areas is estimated using empirical equations and tail volume coefficients in this design. Some design guidelines to determine wing sweep angle, taper ratio, incidence angle and location are also introduced.

• 한국해양공학회지
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• 제12권2호통권28호
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• pp.87-96
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• 1998

A numerical simulation was done to investigate the performance of thin wings in close vicinity to ground. The simulation is based on Vortex Lattice Method(VLM) and freely deforming wake elements are taken into account for a sudden acceleration case. The parameters covered in the simulation are angle of attack, aspect ratio, ground clearance, sweep angle and taper ratio. In addition, the effect of the wing endplate on the ground effect is included. The wing sections used for present computations are uncambered, cambered and S-types. The present computational results are compared with other published computational results and experimental data.

• Food Science and Biotechnology
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• 제16권6호
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• pp.1069-1071
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• 2007

The frequency independent critical concentration (Cc) of xanthan and carob (X/C) mixed gel was determined based on the Winter-Chambon's theory. X/C mixed (X/C=1:1 ratio) gels were prepared from 0.1 to 1% of concentration. The linear viscoelastic properties, i.e., storage and loss modulus, of X/C mixed gel at $20^{\circ}C$ were measured by frequency sweep tests. The frequency independence of tangent function of phase angle (tan ${\delta}$) of X/C mixed gels was graphically determined from the intersection of the plot of phase angle against concentration at varied frequencies. The intersection (C=0.43%) was considered to be Cc of X/C mixed gel.

• 한국운동역학회지
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• 제18권1호
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• pp.213-226
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• 2008

본 연구의 목적은 유도의 기본 기술인 당기기, 후리기 훈련 및 측정이 가능한 사람-받기(파트너) 역할을 대신할 수 있는 장비인 유도 인형(doll-uke, 장비-받기)을 개발하는데 있다. 기본 방향은 사람-받기와 최대한 유사한 구조와 기능을 갖도록 하고, 절차는 [기본 모형 설계-제작-평가(1)-모형(2) 평가(2)-1차 제작-보완-2차 제작-보완-평가(3)-완성(최종 제작)- 데이터 취득 장치 연결-완성]의 단계를 거쳤다. 평가는 사람-받기와 장비-받기를 상대로 하는 경우, 당기기 밧다리후리기 동작에 대한 역학적 유사성을 위해 각 변인의 상대수준차를 계산하였으며, 선수들과 지도자의 설문 평가 단계를 거쳤다. 개발된 장비-받기의 구조는 크게 유도인형(doll-uke)과 힘 측정시스템(doll-uke fore system)이다. 밧다리후리기 발휘, 시 사람을 대신한 장비-받기의 역학적 변인들에서 재현율이 관찰되었으며, 동작 패턴이 사람-받기의 유사함과 설문 평가에서도 유용성이 인정되었다. 사람-받기를 대신할 훈련 및 측정 장비인 유도 인형(doll-uke)을 이용함으로서 당기기 밀기 후리기 등의 기술 강화는 물론, 동작 시 발휘되는 힘의 정량적 데이터를 용이하게 얻어 선수들에게 피드백을 제공해줌으로써, 정성적 정량적 분석을 통한 훈련 현장의 과학화, 경기력 향상을 기대할 수 있겠다.

• Wind and Structures
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• 제31권3호
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• pp.229-240
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• 2020

In the present work, the main features of primary vortices and the vorticity concentrations downstream of vortex bursting in crossflow plane of a delta wing with a sweep angle of Λ=70° were investigated under the variation of the sideslip angles, β. For the pre-review of flow structures, dye visualization was conducted. In connection with a qualitative observation, a quantitative flow analysis was performed by employing Particle Image Velocimetry (PIV). The sideslip angles, β were varied with four different angles, such as 0°, 4°, 12°, and 20° while angles of attack, α were altered between 25° and 35°. This study mainly focused on the instantaneous flow features sequentially located at different crossflow planes such as x/C=0.6, 0.8 and 1.0. As a summary, time-averaged and instantaneous non-uniformity of turbulent flow structures are altered considerably resulting in non-homogeneous delta wing surface loading as a function of the sideslip angle. The vortex bursting location on the windward side of the delta wing advances towards the leading-edge point of the delta wing. The trajectory of the primary vortex on the leeward side slides towards sideways along the span of the delta wing. Besides, the uniformity of the lift coefficient, C_L over the delta wing plane was severely affected due to unbalanced distribution of buffet loading over the same plane caused by the variation of the sideslip angle, β. Consequently, dissimilarities of the leading-edge vortices result in deterioration of the mean value of the lift coefficient, C_L.

• 한국항공우주학회지
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• 제40권12호
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• pp.1017-1024
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• 2012

깃끝단 후퇴각을 가지는 최신 터보프롭 항공기의 프로펠러 블레이드에 대한 공력설계 및 해석을 수행하였다. 프로펠러 형상 설계를 위한 익형은 HS1 계열을 적용하였다. 와류-깃요소 이론(Vortex-Blade element theory)을 기반으로 하고 최소에너지 손실 조건을 만족하는 Adkins의 방법을 적용하여 Conventional 프로펠러 블레이드에 대한 공력설계 및 성능해석을 하였다. 목표 항공기의 설계점에서 코드 길이와 피치각을 변경해 가며 프로펠러 형상을 생성하였다. Conventional 프로펠러 블레이드 형상 정보를 기반으로 코드 길이, 깃끝단 후퇴각을 수정 적용하여 최신 프로펠러를 설계하였다. 전산유체역학을 이용한 설계된 최신 프로펠러 공력특성 분석을 통하여 최신 프로펠러가 적절하게 설계되었음을 확인하였다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1998년도 춘계학술대회논문집; 용평리조트 타워콘도, 21-22 May 1998
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• pp.386-391
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• 1998

The effect of the changes in parameter angles(precone, droop, sweep) on the lead-lag damping was focused on. Experiment was made with hingeless 4-blade rotors and NACA 0012 airfoil. For the measurement of the rotating natural frequencies and lead-lag damping, non-rotating swash plate was oscillated at the regressing lag mode frequency and the data were acquired after the excitation was cut off. Analysis was made using a finite element formulation based on Hamilton's principle. The main blade is assumed as elastic beams. Quasi-steady strip theory is used to obtain aerodynamic forces, and non-circulatory forces are also included.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1999년도 유체기계 연구개발 발표회 논문집
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• pp.221-226
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• 1999

Three-dimensional flow analysis and numerical optimization methods are presented for the design of an axial-flow fan. Steady, Incompressible, three-dimensional Reynolds-averaged Wavier-Stokes equations are used as governing equations, and standard k-$\epsilon$ turbulence model is chosen as a turbulence model. Governing equations are discretized using finite volume method. Steepest descent method, conjugate gradient method and BFGS method are compared to determine the searching directions. Golden section method and quadratic fit-sectioning method are tested for one dimensional search. Objective function is defined as a ratio of generation rate of the turbulent kinetic energy to pressure head. Sweep angle distributions are used as design variables.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1999년도 유체기계 연구개발 발표회 논문집
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• pp.252-256
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• 1999

In this research, the performance predictions of the submersible mixer were investigated. The variation of the performance characteristics by changing the impeller design parameters were discussed through the flow calculation results by using a commercial program, FLUENT. The performance of the submersible mixers is related to the velocity diffusion profiles downstream of the impeller and also the required input motor power to mix the fluid. In this study, the various design parameters such as the number of blade, the hub and tip diameters, the impeller blade profiles and revolution speed of the blades were taken for the fixed values. The blade sweep direction, the chord length distribution along with the radius of the blade and the inlet blade angle were changed to make different testing models. The flow calculation results show the effect of the changed design parameters on the performance of the submersible mixers and also give some helpful information for designing more efficient submersible mixers.

• 수산해양기술연구
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• 제38권3호
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• pp.234-240
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• 2002

본 연구에서는 전개판의 영각 변화에 따른 정적안정성에 관하여 이론적 해석을 하였다. 또한 전개판의 형상별 유체력에 의한 정적 안정성을 평가하기 위하여 종횡비가 다른 평판과 만곡도가 다른 종만곡판을 사용하여 회류수조에서 유체력 및 모벤트를 측정하고 형상별 압력중섬계수와 모멘트 계수를 계산하였다. 본 연구에서 얻어진 결과를 요약하면 다음과 같다. 1. 전개판의 영각($\alpha$) 변화에 따른 끌줄의 장력과 후릿줄의 장력에 의한 모멘트 변화는 전개판을 항상 정적 안정성을 가지도록 작용한다. 2. 종횡비(λ)가 0.5, 1.0, 1.5인 평판의 압력중심계 수는 영각의 증가와 함께 전연에서 중심쪽으로 이동한다. 이것은 유체력에 의한 모멘트는 항상 정적으로 안정하도록 작용한다는 것을 의미한다. 3. 종횡비가 일정(λ=1.5)하고, 만곡도(CR)가 5%, 10%, 15%, 20%인 만곡판의 유체력에 의한 압력중심계수는 영각의 증가와 함께 후연에서 전연쪽으로 이동한 다음, 다시 만곡판의 중심쪽으로 이동한다 만곡판에 작용하는 유체력에 의한 모멘트는 만곡도가 커질수록 정적으로 불안정한 영각의 범위가 증가한다.