Abstract
Super-Sonic Transportation is provided with a thin and low-aspect-ratio wing on which shock waves do not appear till high Mach number and hardly causes the flow separation. If the shock-induced separation dose not appear, the flap might oscillate divergently in a single degree of freedom. This phenomenon is called as “Region B Aileron Buzz.” It is a basic and important research to investigate the shock wave movement caused by the flap oscillation. The present study numerically simulates the flow around a two-dimensional thin airfoil with an oscillating flap. The fluctuations of the flap hinge moment (FHM) are strongly influenced by not only the mean shock wave position but also the region of the shock wave movement. The imaginary component of FHM shows the maximum value when the shock wave oscillates only on the flap. The energy produced by FHM also shows the maximum under this flow structure.
