| タイトル | In-flight boundary-layer transition measurements on a swept wing |
| 著者（英） | Ahmed, Anwar; Wentz, William H.; Nyenhuis, R. |
| 著者所属（英） | Cessna Aircraft Co.|Texas A&M Univ.|Wichita State Univ. |
| 発行日 | 1989-11-01 |
| 言語 | eng |
| 内容記述 | Flight tests were conducted at three different altitudes to detect transition on a smoothed test region of a swept-wing business jet wing using surface hot-film sensors and sublimating chemicals. Strong influence of sweep angle on transition location was observed when the aircraft was flown at some sideslip conditions to simulate changes in effective wing sweep angle. No effects of engine noise on transition were measured when different engine power settings were used. Flight instrumentation and ground data analysis techniques are described. Correlation was obtained between the hot-film sensor signals and sublimating chemicals for transition detection. Crossflow vortices were observed for one flight condition. Results of analyzed data for various flight-test conditions are presented. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 90A13017 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/359997 |
