Flow Visualization Studies of the Mach Number Effects on the Dynamic Stall of an Oscillating Airfoil
MetadataShow full item record
Compressibility effects on 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 freestream Mach number and reduced frequency on the dynamic stall vortex. This study shows that a dynamic stall vortex always forms and convects over the airfoil upper surface at approximately 0.3 times the freestream velocity for all cases studied. The results also demonstrate that occurrence of deep stall is delayed to higher angles of attack with increased reduced frequency, even when compressibility effects are present, but increasing Mach number alone has the opposite effect.
(AIAA Paper 89-0023) Journal of Aircraft, Vol. 27, No. 6, pp. 516-522, Jun. 1990.The article of record as published may be found at http://dx.doi.org/10.2514/3.25313
Showing items related by title, author, creator and subject.
Effects of interfacial debonding and fiber breakage on static and dynamic buckling of fibers in matrices. Serttunc, Metin (Monterey, California. Naval Postgraduate School, 1992-09);Analyses were performed for static and dynamic buckling of a continuous fiber embedded in a matrix and fiber breakage in order to determine the effects of interfacial debonding on the critical buckling load and the domain ...
Chandrasekhara, M.S. (1994-12-23);A three year effort to study the "Compressibility Effects on the Control of Dynamic Stall of Oscillating Airfoils" was funded by ARO in 1990. A fourth year extension was granted for the project. As part of this research, ...
Chandrasekhara, M.S.; Carr, L.W. (1995);A review of experimental results from an ongoing study of the effects of compressibility on dynamic stall of an oscillating NACA 0012 airfoil is presented. The study shows that compressibility effects become significant ...