Accession Number:

AD0632829

Title:

AN INVESTIGATION OF THE AEROELASTIC STABILITY OF THIN CYLINDRICAL SHELLS AT TRANSONIC MACH NUMBERS

Descriptive Note:

Technical rept. for 27 Dec 1965-10 Jan 1966

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1966-05-01

Pagination or Media Count:

38.0

Abstract:

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.

Subject Categories:

  • Fluid Mechanics
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE