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+clc
+Ax = 18.75 // cross sectional area in divergent part in m^2
+A_ = 12.50 // throat area in m^2
+AA_ = 1.5 // Area ratio
+Pxox = 0.159 // pressure ratio from table
+R = 0.287 // Gas constant
+Pox = 0.21e03 // pressure in kPa
+Px = Pxox*Pox // pressure calculation
+// from the gas table on normal shock
+Mx = 1.86 
+My = 0.604 
+Pyx = 3.87 
+Poyx = 4.95 
+Poyox = 0.786
+Py = Pyx*Px
+Poy = Poyx*Px
+My = 0.604
+Ay_ = 1.183
+A2 = 25 
+Ay = 18.75
+A2_ = (A2/Ay)*Ay_
+// From isentropic table 
+M2 = 0.402
+P2oy = 0.895
+P2 = P2oy*Poy
+syx = -R*log(Poy/Pox) // sy-sx
+
+printf("\n Example 17.5\n")
+printf("\n Exit Mach number is %f ",M2)
+printf("\n Exit pressure is %f kPa",P2)
+printf("\n Exit Stagnation pressure is %f kPa",Pox-Poy)
+printf("\n Entropy increase is %f kJ/kg K",syx)
+//The answers vary due to round off error
+