An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 37 MPam. It has been determined that fracture results at a stress of 206 MPa when the maximum (or critical) internal crack length is 2.58 mm. a) Determine the value of Yσπa for this same component and alloy at a stress level of 267 MPa when the maximum internal crack length is 1.29 mm.

we are supposed to determine the stress level at which a wing component on an aircraft will fracture for a given toughness of  and maximum internal crack length , given that  fracture

occurs for the same component using the same alloy at one stress level and another internal crack length  (2.58 mm). It first becomes necessary to solve for the parameter Y for the conditions under which fracture occurred , therefore

do you have any options?