In the present report, with the aid of the usual computation methods, a rotor is investigated the pitch of whose blades is capable of being controlled in such a manner that it varies linearly with the flapping angle. To test the effect of this linkage on the aircraft performance, the theory is applied to an illustrative example.
Aerodynamics of Rotating-wing Aircraft with Blade-pitch Control
1940-02-01
Miscellaneous
No indication
English
Aerodynamics of rotating-wing aircraft with blade-pitch control
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