J. Sides, J.C. Boniface

An implicit space-centered Euler solver due to A. Lerat, and previously developed, at ONERA, for the calculation of steady transonic flows around airfoils and wings, is used here for the numerical simulation of steady compressible flows around helicopter rotor blades. For an extension to the problem of a multibladed rotor in hovering-flight, the method is formulated in a rotating frame attached to the blades, using the pseudounsteady system of the Euler equations derived by assuming that the total rothalpy is constant. The basic 3D wing code is first applied to the calculation of the steady flow past a wall-mounted half wing with swept tip shape, simulating the transonic flow occuring at the tip of a helicopter rotor blade. Then, preliminary numerical results concerning the two-bladed model rotor of US-Army in hovering-flight, and obtained in the framework of a global rotor calculation without wake modelling, are presented and compared with experimental data.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 19 Seiten

DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Dieser Aufsatz ist nicht Teil der Veröffentlichung!

transonic flow, aerodynamics, helicopters, rotor body interactions

Bestellbar

1991