| タイトル | Dynamic stall effects and applications to high performance aircraft |
| 著者（英） | Brandon, Jay M. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1991-03-01 |
| 言語 | eng |
| 内容記述 | Recent research conducted at the NASA Langley Research Center on the effects of large amplitude pitching motions on the aerodynamic characteristics of modern fighter aircraft configurations is highlighted. Wind tunnel tests were conducted on simple flat-plate wings to gain understanding of the complex flow phenomena during unsteady motions at high angles of attack. Studies then progressed to a representative modern fighter configuration. Using a computer controlled dynamic apparatus, tests were conducted to investigate effects of pitch rate and motion time history and to determine the persistence of unsteady effects. Data were also obtained in sideslip and with control surface deflections to investigate dynamic effects on lateral stability and available control power. Force and moment data were obtained using a 6-component internal strain-gage balance. To aid in the interpretation of the results, flow visualization using a laser light-sheet system was also obtained. Results of these tests are discussed, along with their implications on the maneuverability of future advanced airplanes designed to operate in the highly dynamic, high angle-of-attack environment. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 91N22106 |
| 権利 | Copyright, Distribution within the U.S. granted by agreement |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/232293 |
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