A two-dimensional compressor cascade is tested in air (y = 1.4, Cp = 1004.5 J/kgK) with an inlet stagnation pressure of 1 bar and an inlet stagnation temperature of 300 K. For an inlet Mach number of 0.75 and an inlet flow angle of 50 , the exit flow angle is measured as 15.8. Determine the mass flow rate per unit frontal area. Assuming the flow is isentropic, calculate the exit Mach number and the static pressure ratio across the cascade. For the exit Mach number you will likely end up with a non-linear function that you will need to solve using some sort of root finder - or by hand.