Question 1: The figure below has claimed drag coefficients for some simple 3D shapes at Re~104-106. Run Fluent simulations for shapes 1 a sphere, 3, a half sphere with the cut-plane facing downstream, 8 a hemisphere with the cut plane facing upstream, a cube angled 45⁰, 6 a cone with half-angle 30⁰, and 11 a cube with a face perpendicular to the incoming flow at Reynolds number of 500,000. What do your simulations derive the drag coefficients to be? Explain any discrepancies as best as you can.

Question 2: Run a 3D simulation of a rectangular wing with aspect ratio 5 and a NACA0012 airfoil shape at Re=1.5e6 based on the chord length and Ma=0.12. Find Cd and Cl values for the airfoil at angles of attack of 0⁰, 3⁰, and 8⁰. For the 8⁰ case, plot the pressure coefficient along the upper and lower surface of the wing at mid-span. What happens to the drag and lift coefficients when the aspect ratio is increased to 10 (at 8⁰).