An Investigation of the Aeroelastic Stability of Thin Cylindrical Shells at Transonic Mach Numbers

摘要

Static pressure and boundary-layer data were obtained over a rigid pressure shell at Mach numbers from 1.20 to 1.50 and Reynolds numbers from 1.04 to 4.20 x 10 to the 6th/ft in the 16-ft transonic tunnel. These data were obtained with and without addition of air into the boundary layer through a circular slot upstream of the test shell. Flutter characteristics of thin cylindrical shells were obtained at Mach numbers of 1.20 and 1.50 with and without boundary-layer blowing and shell axial loading. Spirally traveling waves appeared on three of the shells just prior to divergent flutter, which was initiated by reducing shell cavity pressure. (Author)