Induced Aerodynamics of Helicopters: Part III
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 1 April 1956
Abstract
HELICOPTER performance methods currently in use fall into two main groups. The smallest is typified by Refs. and, and evaluates performance by considering the forces acting on each element of the blade. To do this it is first necessary to determine the flapping and pitch angles of the rotor, and then to integrate the elemental forces. The equations thus developed are much too complicated for design office use, and simplifications such as Ref. are achieved only at the expense of limiting the work to untwisted and untapered blades. Moreover the basic theory so far published is incomplete since it is tacitly assumed that the rotor thrust is normal to the no‐feathering axis or the tip path plane.
Citation
Payne, P.R. (1956), "Induced Aerodynamics of Helicopters: Part III", Aircraft Engineering and Aerospace Technology, Vol. 28 No. 4, pp. 123-129. https://doi.org/10.1108/eb032681
Publisher
:MCB UP Ltd
Copyright © 1956, MCB UP Limited