| タイトル | Effects of twin-vertical-tail parameters on twin-engine afterbody/nozzle aerodynamic characteristics |
| 本文（外部サイト） | http://hdl.handle.net/2060/19830016207 |
| 著者（英） | Bare, E. A.; Leavitt, L. D. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1983-05-01 |
| 言語 | eng |
| 内容記述 | The Langley 16-foot transonic tunnel was used to determine the effects of several empennage and afterbody parameters on twin-engine aft-end aerodynamic characteristics. Model variables included twin-vertical-tail cant angle, toe angle, airfoil camber, and root-chord length and afterbody/engine interfairing shape. Tests were conducted over a Mach number range from 0.6 to 1.2 and over an angle-of-attack range from 2 deg to 10 deg. Nozzle pressure ratio was varied from 1.0 (jet off) to approximately 10.0. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 83N24478
NASA-TP-2158
L-15570
NAS 1.60:2158 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/162663 |
