EXPERIMENTAL INVESTIGATION AT MACH NUMBER 3.0 OF EFFECTS OF THERMAL STRESS AND BUCKLING ON FLUTTER CHARACTERISTICS OF FLAT SINGLE-BAY PANELS OF LENGTH-WIDTH RATIO 0.96

摘要

Flat, single-bay, skin stiffener panels with length-width ratios of O.96 were tested at a Mach number of 3.0, at dynamic pressures ranging from 1,500 to 5,000 pounds per square foot, and at stagnation temperatures from 500° F to 660° F in order to investigate the effects of thermal stress and buckling on the flutter of such panels. The panel supporting structure allowed partial thermal expansion of the skins in both the longitudinal and lateral directions. Panel skin material and skin thickness were varied.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, where a panel is most susceptible to flutter. The flutter region consisted of two fairly distinct sections, a large-amplitude flutter region and a small-amplitude flutter region.