Transonic vortex airfoil interaction tests at Mach numbers ranging from 0.68-0.86 and airfoil Reynolds numbers of 3.8-5.5 million were conducted in the high Reynolds number, transonic Ludwieg tube wind tunnel. The scheme involves positioning a lifting wing (vortex generator) upstream of a NACA 0012 airfoil so that the trailing vortex interacts with the downstream airfoil. Tests were performed at several vortex strengths as well as several vortex core heights above the downstream airfoil. The results obtained from these experiments indicate a substantial change in the pressure distribution of the airfoil, a spanwise drift of the vortex core as it passes over the trailing airfoil similar to the results observed previously in low speed wind tunnel tests conducted at UTA, and a high degree of unsteadiness in th vicinity of the vortex core. Keywords: Transonic aerodynamics; Blade vortex interaction; Reprints.
Experimental Investigation of the Perpendicular Vortex-Airfoil Interaction of Transonic Speeds
1987
12 pages
Report
No indication
English
Aerodynamics , Vortices , Transonic flow , Rotor blades(Rotary wings) , Airfoils , Blades , Cores , Downstream flow , Drift , High rate , Interactions , Lift , Pressure distribution , Reprints , Reynolds number , Strength(General) , Trailing vortices , Tubes , Vortex generators , Wind tunnels , Wings , Transonic wind tunnels , Helicopter rotors , Transonic characteristics , NACA-0012 airfoils , Ludwieg tube wind tunnels