| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 96 === As a result of fossil energy impact, how to make an effective propulsion system becomes an important topic in the aviation industry. However, many design and analysis methods for propellers are mostly based on simple theories. The lack understanding of the propeller flowfield results in higher cost and development time with lower performance. The purpose of this study is to establish a test platform of UAV propeller performance with numerical analysis method implemented to compare the accuracy.
The advanced propeller SR3 developed by NASA is analyzed numerically using CFD method. The result is compared with the data from related experiment to verify the accuracy of the numerical tool. The goal of the study is to gradually build up a design, analysis and test technical procedure for UAV power system. The present computational theory and numerical method is based on the the CFX numerical software, which solves 3-D Navier-Stokes equations with SIMPLE algorithm, skew upwind differencing scheme, finite volume method and finite element approach. The k-εturbulence model is adopted to simulate the turbulent flowfield. The self-adjusted tetrahedral non-structural grid system is constructed based on the ICEM software. The simulated propeller flowfield and performance compared reasonably well with available test data.
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