The total pressure losses have been made dimensionless with the ideal exit dynamic pressure to give a loss coefficient C_pte. A constant area mixing analysis was then made at x/c=1.3 to give the mixed-out losses as a function of Reynolds number (inlet velocity and axial chord). These show a sharp change at about Re=50,000. Below this Reynolds number the flow is highly separated and the losses are 2 to 3 times the losses at high Reynolds numbers.

The exit flow angle has been calculated in two ways: based on the mixed-out velocity components, and based on the mass-averaged velocities. The analysis was done for the results 30% of an axial chord downstream of the trailing edge (the end of the contour plots above).
At Re=66,000 and above, the mixed-out and mass-averaged angles are the same, and at or slightly below the blade exit angle of 26 degrees.
At Re=44,000 and below, the mixed-out angles increase to about 1 degree above the blade exit angle. The angles based on the mass-averaged velocity components reflect more what is seen in the total pressure loss contours above. For cases A to F, the flow is separated at x/c=1.3 and the deviation is high, about 10 to 15 degrees.

Solution Convergence. It is difficult to obtain steady flow solutions for the highly separated cases due the very low mean velocity in the separation region. The downstream wake oscillated in size over a number of solution procedure iterations. Our level of success in obtaining steady flow solutions is reflected in the "variation" lines (orange and pale green), giving the minimum and maximum values obtained over a large number of iterations, after the solution reached a cyclic state. It should be noted that large separation regions are physically sensitive to flow convergence due to endwall boundary layers, and to limited-blade-number cascade configurations with tailboards or downstream bounding walls; these were not included in the present 2d calculations.