Exercise 3 A thin flat wing with chord length C=1m and span S=10m is at an angle of attack = 5 in a free stream flow, with far field velocity V-300m/s, ambient pressure po = 105 Pa and density p = 1kg/m. The flow is attached around the airfoil and the pressure coefficient Cp = P-Poo 0.5 pv is: varying with x2 m2' x along the upper surface (up) of the airfoil as cup = 0.1 +0.4-0.4 and is constant at the lower surface (dn) of the airfoil with Can = 0.2. Provide a sketch of the configuration and the distribution of the pressure along the flat wing. i. ii. Find the force acting at the top surface of the wing iii. Find the force acting at the bottom surface of the wing iv. Find the Lift and the Drag v. Find the Lift and Drag coefficient vi. Find the CI/CD ratio Note: In real life applications Cp presents predominantly negative values (under-pressure) at the lean (upper) side and positive or negative values at the upwind (down) side.