Vortex interaction on a canard-wing configuration /
W. Calarese.
Description
- Language(s)
-
English
- Published
-
Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1986.
- Summary
-
This 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 tufts, oil, and laser light sheets were 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 general 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. Keywords: Vortex flow; Subsonic flow; Close-coupled canards; Vortex shedding.
- Note
-
"Final Report for Period October 1982 - March 1985."
"October 1986."
- Physical Description
-
xv, 250 pages :
illustrations ;
28 cm.
Viewability
| Item Link |
Original Source |
|
Full view
|
Technical Report Archive & Image Library
|