PROBLEMS resulting from increased temperature associated with flight at supersonci speeds, the serious effects of aerodynamic heating on material properties, and the ultimate strength of assembled structures are discussed in this paper.
Ways are outlined which will alleviate the intrinsic weight penalties accompanying the use of high-density alloys at elevated temperatures. Primarily, this can be accomplished by the proper selection of materials and the choice of more suitable structural configurations.
Suggestions are made how to lessen the peaks of thermal stresses induced by temperature gradients during the interval of transient heating.
The need for efficient stabilization of compression panels subjected to thermal environment is pointed out in a general way; and recent innovations which might accomplish this purpose are then discussed with special regard to thin wing and fuselage design. Also mentioned are the more serious production problems arising from the change-over to high-temperature alloys.