Experimental Study of Flow Control on a NACA 65(2)-415 Airfoil with a Dual Cavity Synthetic Jet

摘要

An experimental investigation is conducted on control of flow over a NACA 65(2)-415 airfoil with a dual cavity synthetic jet. The synthetic jet uses only one bi-morphic piezoelectric disk, but has two resonating cavities and two slits where jets form. The synthetic jet is integrated into the airfoil with one slit tangent to the surface on the suction side at 60% chord and the other slit perpendicular to the chord line on the pressure side at 87% chord. Experiments are conducted in the SDSU low-speed windtunnel. A model with a span of 4.6 chord lengths and endplates ensures a nominally two-dimensional flow over the airfoil. Twelve dual cavity synthetic jets are integrated across the span. It was shown that the synthetic jet significantly affects lift and drag in the Reynolds number range form 50k to 200k. At Re=50k, the lift can increase by as much as 100% and the drag can reduce by as much as 60%.