The circumferential (hoop) stress, h, is given as h=2tpD. The fuselage skin of the Comet was a high-strength aluminum alloy, 0.91mm thick. The fuselage was approximately 3.7m in diameter and 33m long. Standard atmospheric pressure is 1.013105Pa. (a) At (a), determine the hoop stress in the fuselage in Prob. 1-1 at the cruising altitude of 10,000m(32,800ft). (b) Assume that design details introduce a stress concentration of 3.0. Compute the maximum stress developed