http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
피토튜브 장착위치 선정을 위한 전진 비행하는 헬리콥터 유동장의 CFD 분석
조현구(H.G. Cho),강영진(Y.J. Kang),김성현(S.H. Kim),명노신(R.S. Myong),조태환(T.H. Cho),박영민(Y.M. Park) 한국전산유체공학회 2008 한국전산유체공학회 학술대회논문집 Vol.2008 No.-
A CFD analysis of helicopter flowfield in forward flight is considered as non-trivial issue because of the complexity of vorticity-dominated flowfield. In this work, a study on the selection of the proper location for the installation of the Pitot probe is conducted using a CFD code which can deal with the interaction of rotor blade vortex and body. To describe the flow patterns for rotating rotor blades and body, the sliding mesh scheme is utilized. Pressure distributions and flow patterns are also analyzed to identify regions free from the interaction of body and wake induced from rotor blades.
서지한(J.H. Seo),조현구(H.G. Cho),이동호(D.H. Lee),정성철(S.C. Jung),명노신(R.S. Myong),허환일(H.I. Huh) 한국전산유체공학회 2007 한국전산유체공학회지 Vol.12 No.4
Owing to the rapid progress in manufacturing technology of microscale devices, there are active research works in developing microscale propulsion systems. In this study, gas flows in nozzles with size of milli and sub-millimeter are investigated by using a CFD code based on the Navier-Stokes equations. The prediction results were compared with theoretical results of quasi-one-dimensional nozzle flow and experiment data. In general, theoretical values agree very well with the CFD results. However, theoretical values begin to deviate from the CFD and experimental data for relatively small Reynolds numbers and the nozzle shape with rectangular cross section. The primary reason for this discrepancy is due to the existence of the thick boundary layer at the wall in low Reynolds flows.