Investigation of the unsteady pressure fluctuations on an F/A-18 wing at high incidence

The results of an analysis performed on the unsteady pressure measurements taken from the wing of an instrumented rigid 6% scale model of the F/A-18 aircraft at high angles of attack are described. The experiment was carried out at the Institute for Aerospace Research 1.5-m trisonic blowdown wind tunnel. Space-time cross-correlations of the pressure field were performed on the wing upper surface using different reference transducers. The results are presented in the attached flow region on the inboard portion of the wing, which is under the influence of the leading-edge extension vortex system. The convection velocities of the broadband eddies were computed. The variation of the correlation contours of eddies along a typical skin-friction line is illustrated by an example.