Wake Vortex Control Using Rapidly Actuated Segmented Gurney Flaps

Abstract

A study to assess the potential for using rap idly actuated segmented Gurney f laps, also known as Miniature Tr ailing Edge Effectors (MiTEs) , for active wake vortex alleviation is conducted using a half -span model wing with NACA 0012 shape and an aspect ratio of 4.1 . All tests a re performed with the wing at an 8.9 ˚ angle of attack and chord based Reynolds number of 350,000 . The wing is equipped with an array of 13 MiTE pairs . Each MiTE has a flap that in the neutral position rests behind the blunt trailing edge of the wing, and in the down position extends 0.015 ch ord lengths perpendicular to the freestream on the pressure side of the wing . Measurements of section lift coefficient are made using pressure taps to assess the effect of various MiTE configurations on the spanwise lift distribution . Static and dynamic PI V measurements are made on the trailing vortex to assess the steady -state and transient effects of different actuation schemes . It is found that the MiTE configurations that nearly conserve the total lift on the wing can also displace the vortex by 0.041 chord lengths in the spanwise direction and 0.016 chord lengths in the liftwise direction . These perturbations can be produced at axial wavelengths corresponding to short and long wavelength vortex instabilities.