AN INVESTIGATION OF THE AEROELASTIC STABILITY OF THIN CYLINDRICAL SHELLS AT TRANSONIC MACH NUMBERS
Technical rept. for 27 Dec 1965-10 Jan 1966
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
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 6thft 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.
- Fluid Mechanics