Flat, rectangular aircraft panels are parametrically simulated on operational analog computer as thin elastic plates simply supported over cavity containing still air and exposed to supersonic potential flow parallel to plane of panel; modified-thickness ratio, shown to be primary panel flutter parameter, is determined for length-width ratios between 0.2 and 5.0 and plotted vs length-width ratio to define basic reference panel flutter boundary which is presented along with few nonlinear effects.
Simulation of supersonic aircraft panel aeroelastic instabilities
AIAA -- Tech Papers
Meeting of the AIAA -- Simulation for Aerospace Flight Conference ; 1963 Flutter
1963
8 pages
Aufsatz (Konferenz)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.