Modification of lifting body aerodynamics using synthetic jet actuators

TLDR

A symmetric airfoil derived from a NACA four‑digit series with a cylindrical leading edge was tested at Re≈3×10⁵, and the influence of synthetic jet control location and amplitude on flow separation was studied. Synthetic jet control near the leading edge reattached flow up to 18° AoA, and hot‑wire data revealed transient vortices during the transition from separated to reattached flow.

Abstract

The control of separated flow on an unconventional airfoil using synthetic jet actuators was investigated experimentally. A symmetric airfoil based on the aft portion of a NACA four-digit series airfoil with a cylindrical leading edge was used in the experiment. The tests were conducted at Rec=3(10)5. For a>5°, the flow separated from the airfoil surface. Applying synthetic jet control near the leading edge, upstream of the separation point, reattached the separated flow fixangle of attack up to 18°. The effect of control location and amplitude was investigated for different angles of attack. Hot wire measurements in the nearwake of the airfoil revealed a transient passing of vortices associated with the transition from separated to reattached flow on the airfoil.