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.

Creator(s): Pfluger, A
Creation Date: February 1, 1940
Partner(s):
UNT Libraries Government Documents Department
Collection(s):
National Advisory Committee for Aeronautics Collection
Technical Report Archive and Image Library
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Total Uses: 145
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Date(s):
  • Creation: February 1, 1940
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.

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Serial Title: NACA Technical Memorandums
Partner:
UNT Libraries Government Documents Department
Collection:
National Advisory Committee for Aeronautics Collection
Collection:
Technical Report Archive and Image Library
Identifier:
Resource Type: Report
Format: Text
Rights:
Access: Public
Statement: No Copyright, Unclassified, Unlimited, Publicly available