1367197 Rotor blade; propellers TEXTRON Inc 17 May 1972 [17 May 1971 (2)] 23118/72 Headings B7V and B7W A blade for a convertiplane prop rotor has a unitary structure and its twist and camber vary non-linearly from root to tip, the twist angle between blade chord and a reference plane decreasing linearly from root to an intermediate point and decreasing less severely from that point to the tip, curve 24, Fig. 3, and camber decreasing from the root to an intermediate point and increasing from that point to the tip, curve 25. As a result aerodynamic twist, curve 26, decreases from root to tip, the major change being in the inboard 40% of span. The blade comprises a spar 30 formed from channels 33, 34, 35, and a panel 40, and a trailing section 31 having upper and lower skins 50, 51 with honeycomb units adhesively secured thereto, with the cells substantially perpendicular to the blade chord. The parts are secured by bonding with heat-setting adhesive and as pressure is applied during manufacture the honeycomb units intersect. A fitting (70), Fig. 10 (not shown), in an extension (60) of the spar 30 receives, on needle bearings, a spindle (71) of a hub.
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