Author(s)

A.D'Alascio, A. Visingardi and P. Renzoni

Abstract

An explicit correction to the Kutta condition applied to rotary wing potential flows is described. Indeed, the simple application of the classical steady Kutta condition, which ensures the uniqueness of the solution of the potential flow problems [1,2], is unable to guarantee a zero pressure jump at the blade trailing edge. Several investigations performed on this problem have indicated the presence of considerable non-zero pressure jumps for highly 3D flows (blade root and tip) [3] and for unsteady flows characterized by high reduced frequencies [4]. The application of a Kutta condition correction in CIRA's BEM code RAMSYS [3] has shown the ability to ensure a continuous pressure across the blade trailing edge. 1 Introduction The flow field around h

Keywords