EXPERIMENTAL INVESTIGATION AT MACH NUMBER 3.0 OF THE EFFECTS OF THERMAL STRESS AND BUCKLING ON THE FLUTTER OF FOUR-BAY ALUMINUM ALLOY PANELS WITH LENGTH-WIDTH RATIOS OF 10

摘要

Skin-stiffener aluminum alloy panels consisting of four bays, each bay having a length-width ratio of 10, were tested at a Mach number of 3.0 at dynamic pressures ranging from 1,500 psf to 5,000 psf and at stagnation temperatures from 300° F to 655° F. The panels were restrained by the supporting structure in such a manner that partial thermal expansion of the skins could occur in both the longitudinal and lateral directions.nA boundary faired through the experimental flutter points consisted of a flat-panel portion, a buckled-panel portion, and a transition point at the intersection of the two boundaries. In the region where a panel must be flat when flutter occurs, an increase in panel skin temperature (or midplane compressive stress) makes the panel more susceptible to flutter. In the region where a panel must be buckled when flutter occurs, the flutter trend is reversed. This reversal in trend is attributed to the panel postbuckling behavior.