Induced Aerodynamics of Helicopters: Part III

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