N. Bettschart, R. Hanotel, A. Desopper

Experimental and theoretical studies are presently under development at ONERA on helicopter rotor/fuselage interactional aerodynamics. From the experimental point of view, a test was conducted in the ONERA S2 Chalais subsonic wind tunnel to measure the unsteady velocity field around an Aerospatiale powered helicopter model (Dauphin 365 scaled 1/7.7) in forward flight (µ = .20). The unsteady measurements were performed with a three components laser doppler velocimeter. From the theoretical point of view, an iterative coupling method has been developed for rotor fuselage calculations. This method is based on a panel method (source and doublet singularities) for the fuselage and on a lifting line code for the rotor. These two codes are coupled in an iterative approach through an azimuth marching technique. The experimental results are analyzed and comparisons between experimental and computed results are presented for both the U.S. Army Langley and the ONERA tests. These comparisons show that the fuselage effects have to be taken into account in particular for the rotor wake geometry and for the flow conditions on the inboard part of the blade. Future tests planned with the powered model as well as improvements of the computational method are also briefly described.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 13 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!

aerodynamics, helicopters, rotor body interactions

Bestellbar

1991