EVALUATION OF NEW TITANIUM SHEET ALLOYS FOR USE IN AIRFRAME CONSTRUCTION. VOLUME I. A DESCRIPTION OF THE BASIC OBJECTIVES OF CONTRACT AF 33(600)33597. THE SELECTION OF PARTS FABRICATED UNDER THIS CONTRACT, THE SELECTION OF THE SHEET ALLOYS EVALUATED, AND THE RESULTS OF A PRELIMINARY EVALUATION OF TI-16V-2.KA1 AND TI-4A1-3MO-1V SHEET ALLOYS ARE PRESENTED IN THIS VOLUME
AIR MATERIEL COMMAND WRIGHT-PATTERSON AFB OHIO
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A description is presented of the basic objectives, the selection of parts airframe, the selection of sheet alloys, and the results of a preliminary evaluation of Ti-16V-2Al and Ti4Al-3Mo-1V alloys. On the basis of mechanical property and forming tests, Ti-4Al-3Mo-1V alloy was selected for full evaluation. Although elevated-temperature testing was not extensive, the maximum useful temperature of Ti-16V-2.5Al alloy appeared to be about 700 F because of temperature-stress instability. The creep strength of Ti-4Al-3Mo-1V at 600 and 800 F was significantly higher than that of Ti-16V-2.5Al alloy. Ti4Al-3Mo-1V also appeared to have the better formability.