it is very urgent. In a cascade of a compressor, choking takes place at the inlet Mach number of 0.88 and with the inlet flow angle 15 deg.

Please help me with the following two problems. it is very urgent.

1. In a cascade of a compressor, choking takes place at the inlet Mach number of 0.88 and with the inlet flow angle 15 deg. If the ratio of the throat area to the frontal area, A*/H1s, for the cascade is 0.625, calculate the loss of stagnation pressure between the far upstream and the throat and express this as a loss coefficient. Comment on the cause for this loss.

2. A 2D cascade of a compressor is tested in air with inlet stagnation pressure of 1.1 bar and inlet stagnation temperature of 313K. When inlet Mach number is 0.8 and inlet flow angle is 48 dig, the exit flow angle is measured as 16 deg. For these conditions determine the mass flow rate per unit frontal area. Assume isotropic flow and calculate the exit Mach number and the static pressure ration across the cascade.