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정진덕(Chung, Jindeog),최성욱(Choi Sungwook),이장연(Lee Jangyeo) 한국유체기계학회 2006 유체기계 연구개발 발표회 논문집 Vol.- No.-
Wind tunnel testings to develope tilt-rotor Smart Unmanned Aerial Vehicle (SUAV) were intensively performed. Small wind tunnel was used to find and evaluate design parameters and to fix general layout of configuration. The application of large tunnel with 40% scaled model is to collect performance and stability related aerodynamic data. During large scale model test wind tunnel is used as a tool to compare Flaperon types, to improve lift characteristics by using different height vortex generators and to alleviate nacelle separated flow effects on the wing.
정진덕(Jindeog Chung),홍단비(Danbi Hong) 한국항공우주연구원 2009 항공우주기술 Vol.8 No.1
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 3㎜와 5㎜인 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. To improve the aerodynamic efficiency of Smart Unmanned Aerial Vehicle (SUAV), vortex generators and flow fence are applied on the surface and the tip of wing. The initially applied vortex generator increased maximum lift coefficient and delayed the stall angle while it produced excessive increase in drag coefficient. It turns out reduction of the airplane's the lift/drag ratio. The new vortex generators with L-shape and two different height, 3㎜ and 5㎜, were used to TR-S4 configuration to maintain the desired level of maximum lift coefficient and drag coefficient. Flow fence was also applied at the end of both wing tip to reduce the interaction between nacelle and wing when nacelle tilting angles are large enough and produce flow separation. To examine the effect of flow fence, flow visualization and force and moment measurements were done. The variation of the aerodynamic characteristics of SUAV after applying flow control devices are summarized.
〈기술논문〉 PAV(Personal Air Vehicle) 개발에 필요한 주요 성능 지표들
정진덕(Chung Jindeog),강왕구(Kang Wanggu) 대한기계학회 2010 대한기계학회 춘추학술대회 Vol.2010 No.5
To resolve the current ground traffics congestion PAV(Personal Air Vehicle) is suggested one of the means of future transportation. Various configuration and concept of PAV's are being introduced and couple of PAV's are under flight test. The configuration and aerodynamic characterisitcs, type of propulsion system, structure, control, system requirements of the suggested PAVs are summarized in this paper. And key performance parameters for PAV development considering future technology enhancement are suggested.
정진덕(Chung jindeog) 한국항공우주연구원 2011 항공우주산업기술동향 Vol.9 No.2
지속적인 유가 상승으로 인하여 항공기 운용비중에서 연료비가 차지하는 비율이 계속해서 증가하고 있다. 이러한 문제의 해결책으로는 기존 항공기엔진보다 더 연료 효율이 우수한 엔진의 필요성이 대두가 되었고, 그 중심에는 터보팬 엔진과 프로펠러의 장점을 결합한 Open Rotor 엔진이 있다. 이러한 Open Rotor 엔진개념은 근자에 갑작스럽게 대두된 것이 아니라 1970년대 후반부터 시작한 Advanced Turboprop 프로그램 (ATP)으로부터 시작이 되었다. 본 논문은 1980년대에 ATP 산출물로 개발된 Advanced Propeller를 적용한 SRP(Single Rotating Propeller)와 CRP(Counter Rotating Propeller) 개념과 비행시험을 통하여 파악한 연구결과를 정리하였다. 또한 최근 open rotor 엔진 필요성에 따라 GE와 Rolls-Royce가 수행중인 연구 내용, 그리고 Open Rotor 엔진 개발 성공을 위해서 해결해야 할 기술적인 요소들과 이들을 해결하기 위한 연구에 대하여 정리하였다. Portion of fuel cost in an airplane’s operating cost is continuously increasing due to the current high price of oil. The necessity of new engine which can reduce fuel burn or enhance engine efficiency of existing engines is seeking, and lots of the research works have been going on to resolve this issue. One of the possible solutions is open rotor engine which maximizes the benefits of turbofan engine in high speed operation and propeller efficiency in low speed operation. The concept of open rotor engine is not introduced recently, it might be initiated from the advanced turboprop program(ATP) in 1970’s. In this paper summarized by-product of ATP such as SRP(single rotating Propeller) and CRP(Counter Rotating Propeller) which was backbone of open rotor engine. The current research activities performed by major engine companies such as GE and Rolls-Royce to materialize the concept are introduced, and the technical challenges of open rotor engine and current research works to resolve these issues are also discussed.
[기술논문] 중형급 항공기 동체 크기에 따른 항력 변화
정진덕(Chung Jindeog) 대한기계학회 2013 대한기계학회 춘추학술대회 Vol.2013 No.5
The size of fuselage cross section is absolutely controlled by Market Requirement and Objective. Without a specific design criteria especially seat-abreast for the size of cross section designer can generate the various configurations. The proposed study was performed at the very early stage of aircraft design since the market did not sure what size of cross section should be proposed and its influence on aircraft performance. Three aircraft configurations are generated and the aerodynamic characteristics are evaluated by assuming the size of wing and empennage is identical.