http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
직사각형 평판 날개의 날개짓과 비틀림 운동에 대한 비정상 VLM 공력 해석
김우진(Woo-Jin Kim),김학봉(Hark-Bong Kim) 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.3
직사각형 평판날개의 날개짓과 비틀림 운동을 해석하기 위하여 비정상 와류격자법 (VLM)을 이용하였다. 단순 상하 및 피칭 운동하는 날개에 대한 해석결과를 실험 및 다른 수치해석 결과들과 비교하여 복잡한 날개짓 비행을 모사하는데 본 방법을 사용할 수 있음을 보였다. 날개짓 각 진폭이 20°인 경우에 여러 가지 비틀림 각과 무차원 주파수 변화에 대하여 직사각형 평판 날개의 양력, 추력 및 추진효율을 계산하였다. 계산 결과를 분석하여 주기적으로 변하는 비틀림이 날개짓 날개의 공력 특성에 미치는 영향을 살펴보았다. The unsteady vortex lattice method is used to model twisting and flapping motions of a rectangular flat plate wing. The results for plunging and pitching motions were compared with the limited experimental results available and other numerical methods. They show that the method is capable of simulating many of the features of complex flapping flight. The lift, thrust and propulsive efficiency of a rectangular flat plate wing have been calculated for various twisting angles and reduced frequency with an amplitude of flapping angle(20°). And the effects of the twisting on the aerodynamic characteristics of the flapping wing are discussed by examination of their trends.
논문(論文) : 고 아음속 터빈 깃 주위의 열유동 및 내부 열전달에 관한 수치해석 연구
김우진 ( Woo Jin Kim ),김현식 ( Hyun Shik Kim ),곽재수 ( Jae Su Kwak ),김학봉 ( Hark Bong Kim ) 한국항공운항학회 2010 한국항공운항학회지 Vol.18 No.1
Developments of numerical methods are very important to design and analysis for a high subsonic turbine blade. In general, Analysis by experimental investigation has needed a lot of human resources and required time, indispensably, and equipments still have a limit to measure in conditions of high temperature. Rapid technological developments of CPU and integration level of memory make it possible to advance computation with almost exactly simulation so, recent developments of numerical methods are in spotlight. In the present study, the panel method, which is well-known as relatively simplified numerical method, and 2-dimensional ordinary differential Falkner-Skan equation were computed in order to analyze the outer flow, and FVM-based solid heat transfer equation, was also computed to forecast the temperature distribution of the airfoil and the turbine blade. Unstructured grid was constructed in the turbine blade, which has double cooling holes, in order to analyze the internal heat transfer. Cooling fluid was assumed as fully-developed turbulent flow and that circulated in cooling holes.