B.G. van der Wall, M. Wentrup, G. Rajagopalan, S.N. Jung

A simple analytical model to account for fuselage-induced velocities at rotor blade elements and at rotor wake nodes is described. The method is applied to three different fuselage configurations. Results obtained with a comprehensive rotor code show the fuselage effect on rotor trim controls, comparing the isolated rotor with inclusion of the fuselage for the same trim. This is compared to a simple analytical estimate of the fuse-lage effect using blade element/momentum theory. It is found that in forward flight the lateral control is main-ly affected by fuselage effects. Rotor thrust can be varied by the presence of the fuselage, depending on its angle of attack, and the fuselage influence generally increases with flight speed.

41th European Rotorcraft Forum 2015

Conference Paper

englisch

21,0 x 29,7 cm, 19 Seiten

DGLR-Bericht, 2016, 2016-01, 41st European Rotorcraft Forum 2015; S.-; 2016; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

fuselages;mathematical models;momentum theory;rotors

Bestellbar

2016