| タイトル | A study of roll attractor and wing rock of delta wings at high angles of attack |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940020629 |
| 著者（英） | Niranjana, T.; Pamadi, Bandu N.; Rao, D. M. |
| 著者所属（英） | Vigyan Research Associates, Inc. |
| 発行日 | 1993-12-01 |
| 言語 | eng |
| 内容記述 | Wing rock is a high angle of attack dynamic phenomenon of limited cycle motion predominantly in roll. The wing rock is one of the limitations to combat effectiveness of the fighter aircraft. Roll Attractor is the steady state or equilibrium trim angle (phi(sub trim)) attained by the free-to-roll model, held at some angle of attack, and released form rest at a given initial roll (bank) angle (phi(sub O)). Multiple roll attractors are attained at different trim angles depending on initial roll angle. The test facility (Vigyan's low speed wind tunnel) and experimental work is presented here along with mathematical modelling of roll attractor phenomenon and analysis and comparison of predictions with experimental data. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 94N25111 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/113518 |
