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최원(W. Choi),최재승(J.S Choi),정인면(I.M Jung),김지홍(J.H Kim),이일우(I.W Lee),한성훈(S.H Han),원영수(Y.S. Won) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
Propeller shall have high efficiency and improved aerodynamic characteristics to get the thrust to fly at high speed for the Regional turboprop aircraft. That is way Clark-Y airfoil which is used to conventional turboprop aircraft propeller is selected as a blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the propeller design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point of Regional turboprop aircraft. The propeller design results indicate that is evaluated to be properly constructed, through analysis of propeller aerodynamic characteristics using the Meshless method and MRF, SM method.
MRF 기법을 이용한 초소형 비행체 프로펠러 공력특성 연구
최원(W. Choi),김지홍(J.H Kim),이경태(K.T Lee),박찬우(C.W Park) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
This paper dealt with the flow simulation for the optimum designed propeller for Micro Aerial Vehicle, using a commercial CFD program(FLUENT). The propeller was modeled by the Multiple Reference Frame(MRF) method. For the validation of the computational method, the flow field analysis results for the propeller were compared with the flow analysis results, which are using Xfoil, for the optimum design, and with the wind tunnel data of a similar propeller model. By these validation processes, the reliability of MRF method was confirmed.
담도 ㆍ 췌장 : 9 - 담석내에서 16 S rRNA 증폭을 통한 Helicobacter pylori 의 검출
김인한(I . H . Kim),이돈행(D . H . Lee),최미숙(M . S . Choi),이진우(J . W . Lee),김선후(S . H . Kim),최원(W . Choi),김범수(P . S . Kim),김형길(H . G . Kim),신용운(Y . W . Shin),김영수(Y . S . Kim),신석환(S . H . Shin),이건영(K . Y . Le 대한소화기학회 1999 대한소화기학회 추계학술대회 Vol.1999 No.-
신훈범(H.B. Shin),최원(W. Choi),서석주(S.J. Seo),유진복(J.B. Ryu) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
Ice accretion is one of the potential hazards in airplane flight, adversely affecting aircraft aerodynamic. There are two distinct icing analysis that can be simulated. One is predicting the effect of ice on the aerodynamic performance of airfoils when ice geometry is known. The other is simulating ice accretion. This work presents the method of icing accretion analysis. This work presents an Eulerian approach to calculate the droplet collection efficiency on the 2D airfoil. The initial flow solution are obtained the FLUENT and copled with droplet motion in the ambient condition.