Suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 27 MPa (24.57 ksi). It has been determined that fracture results at a stress of 112 MPa (16240 psi) when the maximum internal crack length is 9.4 mm (0.3701 in.). For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 5.8 mm (0.2283 in.).

For each of the following process: a) sketch the p-v diagram, b)sketch t-s diagram, c) sketch t-v diagram, d) sketch the boundary work on one of the diagrams (a, b or c) and e) sketch the reversible heat transfer on one of the diagrams (a, b or c): 1- isobaric process from compressed liquid to superheated vapor 2- isothermal process from compressed liquid to superheated vapor 3- isentropic process from compressed liquid to superheated vapor