| タイトル | Investigation of the Vortex Tab |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850016898 |
| 著者（英） | Hoffler, K. D. |
| 著者所属（英） | North Carolina State Univ. |
| 発行日 | 1985-05-01 |
| 言語 | eng |
| 内容記述 | An investigation was made into the drag reduction capability of vortex tabs on delta wing vortex flaps. The vortex tab is an up-deflected leading edge portion of the vortex flap. Tab deflection augments vortex suction on the flap, thus improving its thrust, but the tab itself is drag producing. Whether a net improvement in the drag reduction can be obtained with vortex tabs, in comparison with plane vortex flaps of the same total area, was the objective of this investigation. Wind tunnel tests were conducted on two models, and analytical studies were performed on one of them using a free vortex sheet theory. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 85N25209
NAS 1.26:172586
NASA-CR-172586 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/156589 |
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