| タイトル | Tail venting for enhanced yaw damping at spinning conditions |
| 著者（英） | Stough, H. P., III; Fremaux, C. M.; Whipple, Raymond D. |
| 著者所属（英） | Lockheed Engineering and Sciences Co.; NASA Langley Research Center |
| 発行日 | 1991-01-01 |
| 言語 | eng |
| 内容記述 | An investigation was conducted in the NASA Langley 20-ft Vertical Spin Tunnel to determine the spin and spin-recovery characteristics of a 1/11-scale model of a low-wing general aviation airplane with a horizontal tail modified with variable-size gaps to allow ventilation of the vertical stabilizer and rudder. Erect spins at symmetric loadings were tested with varying gap sizes on either or both sides of the horizontal tail. The model results indicate that the basic airplane (with no gaps) exhibits a fast, flat spin from which no recoveries can be obtained. The airplane with the modified tail has either a fast, flat spin from which no recoveries or poor recoveries may be made, or a slower, steeper spin from which fair to excellent recoveries may be obtained, depending on the size and orientation of the tail gaps. The major contribution to spin recovery was from the gap on the leeward side of the tail. Gap widths of 15-25 percent of the tail semispan were needed to produce satisfactory recovery from the flat spin. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 91A53741
AIAA PAPER 91-3220 |
| 権利 | Copyright |
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