| タイトル | Canard-wing vortex interactions at subsonic through supersonic speeds |
| 著者（英） | Rogers, Lawrence W.; Erickson, Gary E.; Schreiner, John A. |
| 著者所属（英） | NASA Langley Research Center|NASA Ames Research Center |
| 発行日 | 1990-01-01 |
| 言語 | eng |
| 内容記述 | The NASA-Ames 6 x 6-foot Transonic/Supersonic Wind Tunnel has been used to conduct a study of canard-wing flowfield interactions at sub-, trans-, and supersonic speeds, giving attention to vortex interactions, vortex breakdown, shock-wave development, and vortex-shock interactions. The results obtained show that the canard-wing flowfield interaction delays vortex breakdown to a higher angle-of-attack at sub- and transonic speeds; while the flowfield interference eliminates shock-induced secondary boundary layer separation on the wing, it does not alter the location and development of a rear shock wave extending laterally across the wing. A canard-induced upwash field accelerates the upward migration of the wing vortex at sub-through-supersonic speeds, but is most pronounced at transonic speeds due to the interaction of the vortical flow with the rear shock wave. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 90A45154
AIAA PAPER 90-2814 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/354654 |
|
