Q2/Using linear theory, it is required to compare the two airfoils shown below. Each airfoi symmetrical and is placed at zero angle of attack with an air stream at a Mach number M. =2 pressure Pe =100 kPa. Determine the Mach numbers and pressures in regions 1, 2 and 3. Wha the value of Cp for each of two airfoils? 3. -0.15 m 0.15 m -0.2 m- 0.1 m 0.3 m- -0.3 m