Project 4 A stress-strain test has been conducted on an aircraft component and the result is tabulated as followed: stress +, psi 40000 30000 20000 10000 , in/in , psi 0.000 0 0.001 10298 0.002 18852 0.003 25882 0.004 31586 0.005 36137 0 0 0.001 0.002 0.003 0.004 0.005 strain +, in/in 2 In this test, it is found that the component fails at the strain of 0.005 in/in. Use the trapezoidal rule and the Gauss quadrature to estimate the strain energy of the component which is required to assess the reability of the aircraft wing system. As a guidance, the curve for the test is given by: =11.25141052