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The resulting compressor blade section is optimized w.r.t.
The folding blade comprises a stall regulated root blade section and a folding tip blade section with the fold axis inclined relative to blade span.
A blade section design procedure was presented using an optimization technique and an alternative procedure for the effective blade section is developed using a lifting surface design method.
Blade section inclination to the inflow was also found to influence power output.
Each design iteration starts with a blade section modification that is impressed on the camber line.
A bending-torsion oscillation problem of a model blade section with structural nonlinearity has been considered in the present study.
Similar(24)
Effective blade sections are two-dimensional sections in two-dimensional flow which have the same chordwise loading distribution as the three-dimensional blade sections of a propeller.
The authors calculated the circulations directly around blade sections, and it is referred as direct method.
This process enables the blade sections to twist appropriately while bending flapwise.
The rotor blade sections are the NACA 66 (MOD) with a = 0.8 meanline.
Some previous attempts at modular blades involved bolting blade sections together, but this created stress points within the blades that make them too weak.
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