Aerodynamic Analysis of Advanced Propellers

• Main Authors: Hwang, Chao-Yueh, 黃朝約
• Other Authors: Shih-H Chen
• Format: Others
• Language: zh-TW
• Published: 1997
• Online Access: http://ndltd.ncl.edu.tw/handle/94895583315072434904

碩士 === 國立成功大學 === 航空太空工程學系 === 85 === The objective of the present research is to study the aerodynamic character-istics of SR2 advanced propellers at steady state low-subsonic speed, and to evaluate the reliability of numerical method by comparing the caculated resultswith experimental data. A finite volume method, with k-e turbulent model, is used to solve the three-dimensional Reynolds-averaged Navier-Stokes equations.The numerical simulation is in the range from advance ratio J=0.7 to 2.1. Forsimplicty and the saving of computational time, single flow channel with assump-tion of steady state and incompressible flow is adopted. The incompressible flowassumption is to have a better correlation with low speed experimental results. The comparison shows that the numerical simulation can correctly predict the advanced propeller performance and flow structure such as swirl flow and tip vortex, etc. Overall, the advanced ratio is a key parameter in the propeller performance.