Accession Number:

ADA179718

Title:

Vortex Interaction on a Canard-Wing Configuration.

Descriptive Note:

Final rept. Oct 82-Mar 85,

Corporate Author:

AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1986-10-01

Pagination or Media Count:

265.0

Abstract:

This experiment studies the interaction of vortices shed by the canard and wings 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 liftdrag ratio. Keywords Vortex flow Subsonic flow Close-coupled canards Vortex shedding.

Subject Categories:

  • Aerodynamics
  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE