For boundary layer flow over the wing of a commercial aircraft is modeled as a straight flat plate with an approximate boundary layer velocity profile of u(y) = V sin (7), 0 y 8 The air stream velocity is 350 ft/sec at 40,000 ft, and the location of interest is x = 10 ft. Assume standard air properties apply. 3. Boundary layer characteristics: (No need to evaluate integrals by hand. Evaluate the final expression using a computer software and provide proof, i.e., printout, screenshot, etc.) (a) Determine the boundary layer thickness, 5. (See lecture slides for laminar or turbulent incompressible flow.) (b) Use the following equation to determine the ratio of the displacement thickness to the boundary layer thickness. dy, 96 (c) Use the following equation to determine the ratio of the momentum thickness to the boundary layer thickness. dy, - (*)(-)-