Richard R. Heldenfels, Eldon E. Mathauser
This paper summarizes some NACA research on the strength and creep of aircraft structural elements and components at elevated temperatures. Experimental data for aluminum-alloy columns, plates, stiffened panels, and multiweb box beams are presented for temperatures up to 600 degrees F and compared with results predicted from materials data. Methods are described for predicting maximum strength from material stress-strain curves and creep lifetime from isochronous stress-strain curves. Some observations on the probable effect of creep on the design of aircraft structures are also included to illustrate the influence of design criteria on the weight of aircraft structures at elevated temperatures.
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