Suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 40 mpa m. it has been determined that fracture results at a stress of 365 mpa when the maximum internal crack length is 2.5 mm. for this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 4.0 mm. 90 mpa

Explanation:

Given:

Strain fracture toughness,

maximum internal crack length in first case,

stress level in the first case,

maximum internal crack length in second case,

stress level in the second case,

So, now we require a factor given as:

Now,

i would think form in reponse to tensional forces

the temperature and the pressure affect solubility. temperature affects by changing the properties of the solvent. the increase in pressure increases solubility, the decrease in pressure decreases solubility.