| タイトル | Hover test of a full-scale hingeless helicopter rotor: Aeroelastic stability, performance and loads data |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840010122 |
| 著者（英） | Warmbrodt, W.; Peterson, R. L. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1984-01-01 |
| 言語 | eng |
| 内容記述 | A hover test of a full-scale, hingeless rotor system was conducted in the NASA Ames 40- by 80-foot wind tunnel. The rotor was tested on the Ames rotor test apparatus. Rotor aeroelastic stability, performance, and loads at various rotational speeds and thrust coefficients were investigated. The primary objective was to determine the inplane stability characteristics of the rotor system. Rotor inplane damping data were obtained for operation between 350 and 425 rpm (design speed), and for thurst coefficients between 0.0 and 0.12. The rotor was stable for all conditions tested. At constant rotor rotational speed, a minimum inplane dampling level was obtained at a thrust coefficient approximately = 0.02. At constant rotor lift, a minimum in rotor inplane damping was measured at 400 rpm. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 84N18190
NAS 1.15:85892
A-9573
NASA-TM-85892 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/160268 |
