| タイトル | An evaluation of the relative merits of wing-canard, wing-tail, and tailless arrangements for advanced fighter applications |
| 著者（英） | Naville, G. L.; Nicholas, W. U.; Huffman, J. K.; Covell, P. F.; Hoffschwelle, J. E. |
| 著者所属（英） | General Dynamics Corp.|NASA Langley Research Center |
| 発行日 | 1984-01-01 |
| 言語 | eng |
| 内容記述 | Two 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. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 84A45013 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/396665 |
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