Question # 5 In the early design the aircraft wing is consider as a spar. In the design, the wing semi- spar is 5m, and is assumed to carry a uniformly

distributed lifting load of 5000 N/m during stead level 5m a) Model the semi-span wing spar using 3 beam element b) Formulate the stiffness matrix of the entire wing spar by assembling the individual stiffness matrix of each element c) Calculate the lifting load that is acting on each node d) Define the boundary conditions, and e) Solve for the loads exerted at the wing root. f) Repeat (a) to (e) by increasing the # of element to 6. (Hint: you may need for write a simple MATLAB code to solve the matrix equation)