| タイトル | Flow visualization studies of the Mach number effects on the dynamic stall of an oscillating airfoil |
| 著者（英） | Carr, L. W.; Chandrasekhara, M. S. |
| 著者所属（英） | NASA Ames Research Center; Naval Postgraduate School; Army Aviation Systems Command |
| 発行日 | 1989-01-01 |
| 言語 | eng |
| 内容記述 | Compressibility effects on the dynamic stall of a NACA 0012 airfoil undergoing sinusoidal oscillatory motion were studied using a stroboscopic schlieren system. Schlieren pictures and some quantitative data derived from them are presented and show the influence of free-stream Mach number and reduced frequency on the dynamic-stall vortex. This study shows that a dynamic stall vortex always forms near the leading edge and convects on the airfoil upper surface at approximately 0.3 times the free stream velocity for all cases studied. The results also demonstrate that initiation of the dynamic stall vortex is delayed to higher angles of attack with increased reduced frequency, but that dynamic stall occurs at lower angles of incidence with increasing Mach numbers. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 89A25019
AIAA PAPER 89-0023
AD-A205029 |
| 権利 | Copyright |
