The wedge angle of the walls in the symmetric nozzle as shown below is 12 degree

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The wedge angle of the walls in the symmetric nozzle as shown below is 12 degree s and the approach Mach number is 2.0. The two oblique shocks emanating from the ramps reflect off one another at the center of the nozzle to form a "slip line" between regions 3 and 4. The reflected shock finally terminates in a normal shock upon reflection off the side wall. Calculate the Mach number in regions 1, 3 and 5 as well as the total (stagnation) pressure ratio with respect to the upstream value for each of these regions.

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