• 한국항공우주학회지
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• 제30권7호
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• pp.150-162
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• 2002

• 한국항공운항학회지
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• 제4권1호
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• pp.87-99
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• 1996

• 한국방재학회지
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• 제9권2호
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• pp.38-46
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• 2009

• 한국항공운항학회지
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• 제5권1호
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• pp.31-50
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• 1997

A new variable wing that can be swept back and forward synchronously were developed to enhance the aerodynamic and stability characteristics of a high speed airplane. The configuration of the new variable wing changes in such a way that inner part of the wing sweeps forward and outer part of the wing sweeps backward, the shift of aerodynamic center of the wing is small, therfore the static margin that is required for the stability of a airplane is not affected. In this study, various configurations of wing models by combined swept back and forward were designed and a wind tunnel tests were conducted to investigate the aerodynamic characteristics of these variable wings. The experimental results showed that the variable wing by combined swept back and forward has no effect on the pitching moment coefficient affecting on an aircraft stability margin and enhance the aerodynamic characteristics for a given approach angle of attack.

• 한국가시화정보학회:학술대회논문집
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• 한국가시화정보학회 2006년도 추계학술대회 논문집
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• pp.149-152
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• 2006

This paper describes the flow visualization around the model of a commercial passenger airplane, Boeing 747-400, which cruises in the transonic speed. The geometry was realized through the reverse engineering based on the photogrammetry. The three-dimensional inviscid steady compressible governing equations are solved in the unstructured grid system under the cruise condition and in a finite volume method. The convective term is processed by the Crank-Nicholson scheme and first order upwind scheme is applied. The lift and drag forces in the wing with engines increase by 1.49% End 3.9%, respectively compared with the wing without engines.

• 경영과학
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• 제18권2호
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• pp.97-105
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• 2001

For the airplane manufacturing industry, to decide the sloe of developing airplane is very important because it affect the developing costs, the type of production industry like national independence production or international cooperation production, etc.. And the decision must be made by the base of national aviation industry, status of technology, economic factors and national and international demand, etc. This paper was studied to present a model for the application of AHP to the decision of optimum size of Korean developing airliner. For this study, a questionnaire was developed In respect to the criteria of developing airliner and given to 50 of professors, researchers and experts who participated in this part. The AHP software developed by Korean Advanced Institute of Science Technology (KAIST) was used to analyze the data.

• 한국항공운항학회지
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• 제28권1호
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• pp.59-65
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• 2020

This paper presents comparative results of configuration modeling and aerodynamic analysis to single-engine airplanes such as C-172, SR-20, and DA40NG. The software OpenVSP was used as an airplane configuration modeling tool. OpenVSP can provide the fastest method to get three-dimensional aircraft configuration from given basic data and drawings of aircraft. Parametric design input in OpenVSP, from given aircraft geometric parameters, was applied to small airplanes mentioned. New aircraft models in this study were reversely designed to coincide with the publicly obtained dimensions of the original aircraft. The basic aerodynamic analysis of newly designed modeling aircraft was performed by the vortex lattice method. Results are shown that the similarity of aerodynamic data obtained except for the lack of DA40NG. In conclusion, the modeling process applied to this work is valuable to obtain conceptual design insight in the reverse design from the small airplanes currently in use for flight training.

• Environmental Sciences Bulletin of The Korean Environmental Sciences Society
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• 제4권4호
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• pp.263-271
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• 2000

To investigate the distribution of air pollutants dispersion in the horizontal wind fields, a chaff release experiment was carried out by an airplane. The temporal and spatial variations of a chaff plume from an elevated point source using the WSR-88D(NEXRAD) radar. The observed profiles of radar reflectivity were compared with the Gaussian diffusion model at slightly unstable atmospheric condition. The present study shows that the distributions of radar reflectivity from chaffs and their concentration by the model are in general agreement with time variation. The dispersion coefficients in downwind($\sigma$(sub)x) and crosswind($\sigma$(sub)y) spread data exceeded what has generally been found at Pasquill and Brigg\`s estimates. As a result, it was clearly shown that horizontal and vertical diffusion coefficients are more accurately determined as compared with theoretical coefficients. At longer diffusion distances(than 10km), a radar observation provided the determination of maximum range and diffusion height more qualitatively, too.

• International Journal of Aeronautical and Space Sciences
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• 제5권1호
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• pp.30-38
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• 2004

This paper deals with a problem of automatic landing guidance and control ofthe longitudinal airplane motion under the wind shear turbulence. Adaptive gainscheduled PID control law is proposed in this paper. Fuzzy logic is the main part ofthe adaptive PID controller as gain scheduler. To illustrate the successful applicationof the proposed control law to the automatic landing control problem, numericalsimulation is carried out based on the longitudinal nonlinear airplane model excited bythe wind shear turbulence. The simulation results show that the automatic landingmaneuver is successfully achieved with the satisfactory performance and the gainadaptation of the control law is made adequately within the limited gains.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제27회 추계학술대회논문집
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• pp.277-280
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• 2006

천음속 영역에서 순항 속도로 비행하는 상용 여객기에 대해 공력을 해석하였다. 실제 여객기의 축소모형을 사진으로 계측하여 역설계하여 형상을 모델링하였다. 사면체로 전체 격자계를 구성하였고 정상 상태에서 압축성 비점성 3차원 Euler 방정식을 풀었다. 날개에 엔진이 장착되었을 때와 제거되었을 때에 대해 계산하였는데 엔진이 장착되면 양력과 항력이 각각 1.49%와 3.9%씩 증가하였다. 또한 날개 표면에서 압력 분포와 엔진 주위의 유동 특성을 밝혔다.