Reynold's Number-Fluid Mechanics Assignment

P5 (20 pts): A diamond wedge with a thickness ratio of 0.07 and a chord length of 1.5m is placed in a free stream of standard sea-level air of Mach 2.5 at an AOA of 5o. Calculate the lift and drag coefficients of the airfoil using the linearized theory. Also, calculate the contribution of the skin friction on the bottom-rear segment of the airfoil to the drag coefficient of the airfoil. Note: for a flat plate of chord c placed at zero-AOA in a free stream of supersonic M., assume a linear relation between Cpr Re, vs. M- that starts at M-0 and has a slope of -0.0505. Cor is the drag coefficient for one side of the plate and Rec is the Reynolds number based on chord c. Take the viscosity at 1.7894e-5Pa's.