| Summary: | 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.
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