| タイトル | A Theoretical and Experimental Investigation of Flap-Lag Stability of Hingeless Helicopter Rotor Blades |
| 本文（外部サイト） | http://hdl.handle.net/2060/19720022353 |
| 著者（英） | Bousman, W. G.; Ormiston, R. A. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1972-08-01 |
| 言語 | eng |
| 内容記述 | The stability of hingeless rotor blade oscillations in hover is examined theoretically using a simplified centrally-hinged, spring-restrained, rigid blade to approximate the deflections of actual elastic blades. The aerodynamic and inertial coupling between the flap and lead-lag degrees of freedom is primarily responsible for instability, however elastic coupling and kinematic pitch-lag coupling both exert a powerful influence on hingeless rotor blade stability. Experimental results obtained from a two-bladed 1.81m diameter model rotor designed for minimum elastic coupling have confirmed the results of linear theory. For this model configuration rotor blade stall at high pitch angles was found to counteract the destabilizing flap-lag coupling and increase the damping of lead-lag oscillations. It was possible to account for this effect with the theory by using drag data for stalled airfoils. |
| NASA分類 | AIRCRAFT |
| レポートNO | 72N30003
NASA-TM-X-62179 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/202745 |
