The present experiment studies the interaction of vortices shed by the canard and wing's leading edges, and their effect on the aircraft aerodynamic characteristics. A close-coupled canard-wing configuration was selected and tested in different wind tunnels and at different conditions. Tunnel and model size effects, Mach number, angle of attack, and spanwise blowing effects on the vortex interaction were analyzed. Intrusive (hot wires) and non-intrusive (laser doppler velocimeters) data acquisition techniques were used and compared to enhance the reliability of the results. Flow visualization by oil flow and laser light sheets was employed. Mean velocities, vortex turbulence intensities, and Reynolds stresses obtained for different conditions were compared and found to be generally consistent. Mach number, wind tunnel, and model size effects were in generall small. Turbulence intensities and stresses increased with angles of attack. Spanwise blowing produced a small favorable effect. The use of a coplanar canard produced a small favorable interaction between the leading edge vortices, while the off-set canard produced a considerable increase in the lift/drag ratio.
Vortex interaction effects on the lift/drag ratio of close-coupled canard configurations
Wirbelwechselwirkungen auf die Steigung/Widerstandsrate von engverbundenen Entenkonfigurationen
AIAA-Papers ; Jun ; 1-13
1987
13 Seiten, 29 Bilder, 8 Quellen
Conference paper
English
Close-coupled canard-wing vortex interaction
AIAA | 1984
|Vortex-Wing Interaction of a Close-Coupled Canard Configuration
Online Contents | 1994
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