| タイトル | Hover test results of a small-scale twin-tilt nacelle model |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850015395 |
| 著者（英） | Schmidt, S. B. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1985-03-01 |
| 言語 | eng |
| 内容記述 | Characteristics in hover of an 11/36%-scale, powered, twin-tilt nacelle model were measured in the NASA Ames Research Center's 40- by 80-Foot Wind Tunnel. The model was powered by two high-pressure air-driven turbofan propulsion simulators. The position of the sting-mounted model was fixed and a movable ground plane was used to vary ground height and orientation. Hover characteristics were investigated in and out of ground effect for roll angles of -2 deg to +14 deg and pitch angles of -15 deg to +10 deg. Results for the basic configurations are compared with data from hover tests of the full-scale tilt nacelle model. Two methods were investigated to increase vertical vane effectiveness: (1) extending the maximum vane deflection from 20 deg to 70 deg, and (2) adding a third vertical vane. The goal was to increase the roll-control capability to significantly reduce or balance the strong, unfavorable rolling moment created by the loss of one engine. Results indicate that the three-vertical-vane configuration is more effective than two vertical vanes and that extended vane deflections significantly reduce the engine-out roll in hover. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 85N23706
NASA-TM-86665
REPT-85061
NAS 1.15:86665 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/156715 |
