Aerodynamics of Rotating-Wing Aircraft With Blade-Pitch Control
Description:
"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" (p. 1).
Date:
February 1940
Creator:
Pflüger, A.
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department