M. Potsdam, M. Smith, T. Renaud

Under the US-France Memorandum of Agreement on Helicopter Aeromechanics, ONERA, US Army, and Georgia Institute of Technology have performed full configuration, unsteady CFD analyses on a Dauphin helicopter configuration using individual, discrete moving blades. The three different multiblock, overset, and unstructured mesh calculations using compressible, unsteady low Mach preconditioning, and incompressible formulations are described. Spatial and temporal convergence studies are reported. Results are compared against ONERA wind tunnel data, including fuselage forces and unsteady surface pressures, rotor thrust, and wake PIV visualizations. Generally good agreement is seen between the partners CFD calculations. At the flight conditions investigated, fuselage force comparisons with data are fair. Comparison of the PIV data with reasonably resolved CFD calculations shows clear qualitative agreement for wake strength and location. The CFD visualizations permit determining the origin of the flowfield structures in the PIV planes oriented streamwise and perpendicular to the mean flow. The flowfield and surface pressure visualizations indicate significant rotor-fuselage-empennage interactions which cannot be seen in lower-order actuator disk models.

35th European Rotorcraft Forum 2009,

Conference Paper

englisch

21,0 x 29,7 cm, 23 Seiten

DGLR-Bericht, 2009, 2009-03, 35th European Rotorcraft Forum 2009 - Conference Proceedings; S.1-23; 2009; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

computational fluid dynamics, rotor body interactions, rotorcrafts

Bestellbar

2009