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diff --git a/3765/CH5/EX5.4/Ex5_4.sce b/3765/CH5/EX5.4/Ex5_4.sce
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+clc
+// Example 5.4.py
+// Consider the flow through a convergent-divergent duct with an exit to throat area
+// ratio of 2. The reservoir pressure is 1 atm, and the exit pressure is 0.95 atm.
+// Calculate the mach numbers at the throat and at the exit.
+
+// Variable declaration
+po = 1.0           // reservoir pressure (in atm)
+pe = 0.95          // pressure at the exit (in atm)
+Ae_by_At = 2.0  // ratio of exit to throat area
+
+// Calculations
+// from table A1 for po/pe = 1.053
+Me = 0.28           // mach number at exit
+Ae_by_Astar = 2.17  // nearest entry
+
+At_by_Astar = 1 / Ae_by_At * Ae_by_Astar // At/Astar = At/Ae * Ae/Astar
+
+// from table A1 for At/A* = 1.085
+Mt = 0.72           // mach number at throat
+
+
+// Results 
+printf("\n Mach number at exit %.2f", Me)
+
+printf("\n Mach number at throat %.2f", Mt)
+