Seven stabilizers were tested at a Mach number of 2 in order to determine the effects of aerodynamic heating and loading on the struc¬tural stability of the stabilizer. The models differed in internal structure and postcure temperatures of the laminated Fiberglas skin. Tests were made at various stagnation temperatures between 440°F and 625°F. The postcure temperatures of the Fiberglas skins were found to affect significantly the ability of the model to withstand the imposed test conditions.
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