G. Barakos, K. Badcock, A. Gagliardi

In this paper a method is presented for the simulation of flow control devices and the assessment of their impact on the aerodynamic performance of helicopter rotors. The current approach is based on performing 2D and 3D CFD calculations using the CFD solver of Glasgow University in combination with a reduced aeromechanics simulation code based on the indicial method. The reduced model is calibrated using CFD data and subsequently used for the simulation of rotor cases. Several flow control devices have been assessed including trailing edge flaps, leading edge slats, Gurney flaps, air jet vortex generators as well as synthetic jets. Having obtained some understanding of the effect of each flow control device on the aerodynamics of the rotor, 3D CFD computations were undertaken for full rotor blades with control devices deployed.

CEAS/KATnet Conference on Key Aerodynamic Technologies, Bremen, 2005

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

DGLR-Bericht, 2005, 2005-07, CEAS/KATnet Conference on Key Aerodynamic Technologies - Proceedings; S.1-8; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

aerodynamics

Bibliothek

2005