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등속도로 하강중인 회전 낙하산의 공력특성에 관한 수치적 연구
제상언(S.E. Je),정성기(S.G. Jung),곽상혁(S.H. Kwag),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2006 한국전산유체공학회지 Vol.11 No.1
In this paper a method for analysing aerodynamic characteristics of a rotating parachute in steady descending motion is presented Because of a complex geometric configuration of the parachute associated with side vents and discontinuous skirts, special procedure was adopted to handle the geometry in the analysis. A panel method was successfully applied to the present problem and yielded good results using above procedure. A CFD code using the full Navier-Stokes equations was also applied and produced good results. Parachute free drop and wind tunnel tests were performed to determine the fully developed canopy configuration and aerodynamic characteristics. The method can be used for optimizing the parachute size and side vent configurations.
제상언(Sang-Eon Je),김도준(Do-Jun Kim),이재명(Jae-Myong Lee),박찬우(Chan-Woo Park),조태환(Tae-Hwan Cho),김진석(Jin-Seok Kim),이진균(Jin-Gyun Lee) 한국항공우주학회 2008 韓國航空宇宙學會誌 Vol.36 No.4
국내 독자 기술로 개발된 KT-1/KO-1 기본 훈련기는 멕시코, 필리핀, 터키, 베네주엘라 등 주요 수출 대상국가의 보유 기본 훈련기 및 무장기에 대한 교체 후보 기종으로 주목받고 있다. 본 연구를 통하여 KT-1 해외수출을 확대하기 위해 동급 기종의 경쟁사를 분석 하고 대륙별 기본 훈련기 보유 현황과 Fade Out 시기를 예측하였다. 시장조사 결과 2025년 까지 33개국에 4,500여대의 소요가 예상 되었으며 자국 항공기 경쟁기종 보유, 정치 외교환경, 경제 환경 등의 고려에 의한 마케팅 가능 국가를 선정하여 수출가능 대수를 예측하였다. The basic Trainer Aircraft of The Korean Air force KT-1/KO-1, which was designed and developed by Korean Technology has been a primary candidate as a replacement for the aging basic trainer or armed version for surface support operation for the nations such as Mexico, Philippine, Turkey, Venezuela and etc. In this study, competitors for the same class aircraft. and the present operational status of the basic trainer of the world were identified and the fade out periods were also predicted. The result of this market analysis showed the required number of aircraft by the year 2025 for 33 countries as 4500. The exportable number of KT-1 aircraft was predicted considering the political/ diploma tical environments, economic environment and also by the ability of producing same class aircraft of the country.
정지비행시 헬리콥터 로터 블레이드의 공력해석 및 최적화
제상언(S.E. Je),정현주(H.J. Jung),김도준(D.J. Kim),조창열(C.Y. Joh),명노신(R.S. Myong),박찬우(C.W. Park),조태환(T.H. Cho) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
In this paper a method for the design optimization for helicopter rotor blade in hover is studied. Numerical analysis of aerodynamic characteristics of the flow around a rotor blade is analysed by usign panel method and CFD code based on Navier-Stokes equation. The result is validated by comparing with existing experimental result. Optimization methods RSM(Response Surface Method) and DOE(Design of Experiments) are applied in combination. The object functions are power, twist angle, taper ratio, and thrust. The optimized result showed a decrease of 17% of the power required.
Ogive-Cylinder 형 첨두부를 갖는 유도무기 주위 고앙각 흐름에서의 비대칭 와류 특성과 이에 따른 측력발생에 대한 수치적 해석 연구
정성기,제상언,명노신,조태환 慶尙大學校 經營行政大學院 2004 工學硏究院論文集 Vol.20 No.-
The demand for continually increased performance of missiles and aircraft leads to considering flight at very high angle of attack where control is very difficult. This is mainly due to shedding of asymmetric vortices from the forebody, producing side forces even at zero sideslip. In this paper, Computational Fluid Dynamics(CFD) was used to analyze characteristic of asymmetric vortices and examine the effects of several cases for rising asymmetric vortices. There are asymmetric grid cluster, sideslip angle and roughness. As a result of the study, asymmetric vortices were sensitive at the areas of roughness and the analysis results coincided with the experiment results at the specified area.