By Grard C.
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Extra resources for Aluminium And Its Alloys
Of aluminium 650° C. t Density of alumina 3-75, of aluminium 2-6. J This system of grading is adopted in the French Aeronautical Specifications, and the analytical methods are given in Appendix I. A variation of 0-25 % in the aluminium content is allowed in Grade I, 0-50 % in Grade II, and 0-75 % in Grade III. CHAPTER I I I MECHANICAL PROPERTIES T H E mechanical properties can be grouped as follows :— A. Tensile Properties: Elongation. Tensile Strength, Elastic Limit, and B. Hardness and Shock C.
100°—150°—200°—250°—300° 5 minutes. Sodium nitrite . 350°—400°—450°—500° 3 minutes. Pqt^ssium nitrate . 550°—600° 1 minute. * C i Appendix IV. Beport of the Conservatoire des Arts et Metiers. No. 13357, January 24th, 1919. 31 MECHANICAL PROPERTIES TEST P I E C E S 0-5 mm. THICK. T Y P E 1A. Tigs. 7, 8, and 9 summarise the results obtained. STAGES OP A N N E A L I N G . Whatever the amount of work, the following stages can be distinguished:— (i) Region of cold work, (ii) Region of softening, (iii) Region of complete anneal, (iv) Region of f alling-off of Elongation.
Area of cross section 10 sq. * Gauge length (for measuring elongation)= \/66-61$ = 3 0 mm. TYPE I B . [Length 100 m m . Between shoulders < Breadth 20 m m . [Thickness 1 mm. Area of cross section 20 sq. mm. Gauge l e n g t h = V 6 6 : 6 7 i = 3 6 m m . TYPE I C . (Length 100 m m . Between shoulders -J Breadth 20 mm. (Thickness 1-5 m m . Area of cross section 30 sq. mm. Gauge l e n g t h = v / 6 6 * 6 7 s = 4 5 mm. * These values are only approximate. , and the exact cross section calculated from these figures.