Investigation of the Aeroelastic Stability of Thin Cylindrical Shells at Subsonic Mach Numbers
Abstract
Boundary-layer and static-pressure data were obtained over a rigid pressure shell at Mach numbers from 0.6 to 0.9 and Reynolds numbers per foot from 300,000 to 5,300,000. These data were obtained with and without the addition of air injected into the boundary layer through a circular slot upstream of the test shell. Static aeroelastic characteristics of thin cylindrical shells were obtained at Mach number 0.9 without the use of boundary- layer control and without shell axial-force loading. An aeroelastic buckling failure was induced on all three shells by reducing the cavity pressure. Flutter of the shell was not encountered during the test.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1971
- Accession Number
- AD0732291
Entities
People
- Warren E. White
Organizations
- Arnold Engineering Development Complex