Experimental studies have been carried out on the aeroelastic stability of several cylindrical shell configurations under various internal stress and supersonic flow conditions. These experiments were conducted in the AEDC Propulsion Wind Tunnel Facility over the Mach number range 1.2 to 3.5. Some of the initial experiments demonstrated that the still-air buckling characteristics of thin cylindrical shells were not significantly influenced by the supersonic air stream. The wealth of still air buckling data can consequently be employed to determine the buckling loads of cylindrical shells exposed to a supersonic flow field. (Author)
Recent Contributions to Experiments on Cylindrical Shell Panel Flutter
1971
17 pages
Report
Keine Angabe
Englisch
SOME RECENT CONTRIBUTIONS TO PANEL FLUTTER RESEARCH
AIAA | 1963
|Some aspects of cylindrical shell panel flutter
AIAA | 1967
|Some aspects of cylindrical shell panel flutter.
AIAA | 1968
|