Materials Science and Engineering: An Introduction

Published by Wiley
ISBN 10: 1118324579
ISBN 13: 978-1-11832-457-8

Chapter 8 - Failure - Questions and Problems - Page 292: 8.7

Answer

$σ_{c} = 134 MPa$

Work Step by Step

Given: Suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane-strain fracture toughness of $26.0 MPa \sqrt m (23.7 ksi \sqrt in.)$. It has been determined that fracture results at a stress of 112 MPa (16,240 psi) when the maximum internal crack length is 8.6 mm (0.34 in.) Required: compute the stress level at which fracture will occur for a critical internal crack length of 6.0 mm (0.24 in.) Solution: Using Equation 8.5, compute the parameter $Y$: $Y = \frac{K_{Ic}}{σ\sqrt πa} = \frac{26.0 MPa \sqrt m}{(112 MPa)\sqrt (π)(\frac{8.6 \times 10^{-3} mm}{2})} = 2.00 $ Using Equation 8.6, we find: $σ_{c} = \frac{K_{Ic}}{Y\sqrt πa} = \frac{26.0 MPa \sqrt m}{(2.00)\sqrt (π)(\frac{6.0 \times 10^{-3} mm}{2})} = 134 MPa$
Update this answer!

You can help us out by revising, improving and updating this answer.

Update this answer

After you claim an answer you’ll have 24 hours to send in a draft. An editor will review the submission and either publish your submission or provide feedback.