An evaluation of the relative merits of wing-canard, wing-tail, and tailless arrangements for advanced fighter applicationsTwo sets of wind tunnel tests were performed to examine the relative merits of wing-canard, wing-tail and tailless configurations for advanced fighters. Both sessions focused on variable camber using automated, prescheduled leading and trailing edge flap positioning. The trials considered a modified F-16 tail and canard configuration at subsonic, transonic and supersonic speeds, a 60 deg delta wing sweep, a 44 deg leading edge trapezoidal wing at subsonic and supersonic speeds, vortex flow effects, and flow interactions in the canard-wing-tail-tailless variations. The results showed that large negative stabilities would need to be tolerated in wing-canard arrangements to make them competitive with wing-tail arrangements. Subsonic polar shapes for canard and tailless designs were more sensitive to static design margins than were wing-tail arrangements. Canards provided better stability at supersonic speeds. The static margin limits were a critical factor in control surface selection. Finally, a tailless delta wing configuration exhibited the lowest projected gross take-off weight and drag values.
Document ID
19840062226
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nicholas, W. U. (General Dynamics Corp. Fort Worth, TX, United States)
Naville, G. L. (General Dynamics Corp. Fort Worth, TX, United States)
Hoffschwelle, J. E. (General Dynamics Corp. Fort Worth, TX, United States)
Huffman, J. K. (General Dynamics Corp. Fort Worth, TX, United States)
Covell, P. F. (NASA Langley Research Center Hampton, VA, United States)