E. Monsen, R. Rudnik

The ability of current CFD tools to predict subsonic and transonic flows around supercritical airfoils with blunt trailing edges is evaluated. Comparisons >between numerical predictions and experimental measurements for a modified RAE 2822 airfoil for one subsonic case and one transonic case are presented. Major influence parameters for the accuracy of the numerical solution are highlighted. A grid refinement study is performed to examine the importance of grid density at critical locations in the flow field. Three two-equation turbulence models are applied to examine the performance of the various model approaches. The results indicate that current CFD tools can reliably produce accurate solutions for this class of flows.

9. DGLR-Fach-Symposium, Erlangen, 1994

Conference Paper

englisch

21,0 x 29,7 cm, 6 Seiten

DGLR-Bericht, 1994, 1994-04, Strömungen mit Ablösung; S.168-173; 1994; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

supercritical wings, transonic flow, subsonic flow, aerodynamics, trailing edges

Bestellbar

1994