Suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 26 MPa (23.66 ksi). It has been determined that fracture results at a stress of 101 MPa (14650 psi) when the maximum internal crack length is 8.7 mm (0.3425 in.). For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 5.2 mm (0.2047 in.).