Abstract
A method for calculating thermal stresses is presented and applied to a solid symmetrical double-wedge steel wing flying at an altitude of 50,000 ft. The wing, after flying steadily at a Mach Number of 1.4 and having a uniform temperature distribution of 531.6°F. absolute, is accelerated at a constant rate of one Mach Number per 30 sec. until a Mach Number of 6.0 is reached. Thermal stresses at the instant the wing reaches a Mach Number of 6.0 are calculated using the elastic properties of steel at room temperature. An interpolation method is presented for estimating the thermal stress during the acceleration.
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