Assume that the airfoil shown below is moving at 175 knots at an altitude of 5 km. Point 1 (=00) 2. Edge of boundary layer The experimentally determined pressure coefficients are Point 2 3 4 5 6 1.00 -2.50 -2.55 +0.16 +0.157 a. [7 Points] What is the Mach number and the Reynolds number for this configuration? Assume that the characteristics dimension for the airfoil is 1.45 m. b. [5 Points] Calculate the local pressure in N/m and in lbf/ft at all five points. What is the percentage change in the pressure relative to the free stream value? Was it reasonable to assume that the pressure changes are sufficiently small that the density is approximately constant? c. [3 Points] Why are the pressures at points 3 and 4 nearly equal and at points 5 and 6 nearly equal? d. [5 Points] At those points where Bernoulli equation can be used validly, calculate the local velocity.