The leading edges of winged hypersonic aircraft are known to be subjected to intense aerodynamic heating (ref. 1) in flight. Detailed research investigations into specific types of leading edges suitable for hypersonic use have been limited. The heat-sink concept, although excessive in weight and limited to short durations of heating (ref. 2), has been the most widely used type of leading edge for hypersonic application. Limited experimental and analytical work on shell types of leading edges (refs. 3 and 4) has been conducted; however, the thermal-buckling behavior of leading edges has been defined only in analytical studies, such as references 5 and 6. These theories include simplifying assumptions, which impose limitations on their applicability to design problems. A series of experimental investigations into the thermal-buckling behavior of flanged, thin-shell leading edges has been conducted at the NASA Flight Research Center, Edwards, Calif.

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