Abstract
Abstract In this study, aerodynamic and structural design of the propeller blade for an advanced turboprop aircraft is performed. Both the vortex theory and the blade element theory are used for aerodynamic design and analysis of the propeller. The propeller must endure various critical loads such as aerodynamic bending, torsion and shear, centrifugal force, vibration, etc. in various flight operations. Therefore the high stiffness and strength carbon/epoxy skin–spar–foam core sandwich type structure is adopted for improvement of lightness. In structural design, the structural design load is selected through investigation of fluid–structure interaction analyses. From investigation of both aerodynamic and structural design results, it is found that the proposed blade has a good aerodynamic performance as well as an allowable structural safety.
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