An experimental study of a two dimensional NACA 0015 airfoil undergoing both positive and negative constant pitch rate motions at high angles of attack was conducted in the Ohio University tow tank facility. Nondimensional pitch rates in the range of 0.1 < K < 0.7 and Reynolds numbers in the range of 141,000 < Re < 342,000 were considered. Test results consist of lift and drag force coefficients and flow visualizations. The results of this study provide insight into the airfoil-dynamic stall vortex interaction during the pitch down motion and the cessation of aerodynamic stall. These data may be useful in high angle of attack applications such as the enhanced maneuverability concept for fighter aircraft. Keywords: Unsteady aerodynamics, Pitching airfoils, Maneuverability. (EDC)
Experimental Investigation of High Lift/High Rate Aerodynamics of an Unsteady Airfoil
1989
49 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fluid Mechanics , Airfoils , Stalling , Unsteady flow , Aerodynamic characteristics , Aerodynamic forces , Aerodynamic lift , Angle of attack , Coefficients , Aerodynamic drag , Jet fighters , Flight maneuvers , Flow visualization , High angles , High lift , High rate , Interactions , Maneuverability , Pitch(Motion) , Reynolds number , Test and evaluation , Vortices , NACA-0015 airfoils , Unsteady aerodynamics , Dynamic stall
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