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+clc
+// Example 5.6.py
+// Consider a convergent divergent nozzle with an exit to throat area ratio of 3.
+// A normal shock wave is inside the divergent portion at a location where the local
+// area ratio is A/At = 2.0. Calculate the exit to reservoir pressure ratio.
+
+// Variable declaration
+Ae_by_At = 3.0 // ratio of exit to throat area
+
+// Calculations
+
+// from table A1 for A/At = 2.0
+M1 = 2.2             // mach number in front the shock
+
+// from table A2 for M1 = 2.2
+M2 = 0.5471          // mach number behind the shock
+po2_by_po1 = 0.6281  // stagnation pressure ratio accross the shock
+
+// from table A1 for M2 = 0.5471
+A2_by_A2star = 1.27  // A2/A2star
+At_by_A2 = 1/2.0     // At/A2
+Ae_by_A2star = Ae_by_At * At_by_A2 * A2_by_A2star //Ae/A2star = Ae/At * At/A2 * A2/A2star
+
+// from table A1 for Ae/A2star = 1.905
+Me = 0.32            // exit mach number
+poe_by_pe = 1.074    // poe/pe
+
+// po = po1 and poe = po2
+pe_by_po = 1 / poe_by_pe * po2_by_po1 // pe/po = pe/poe * poe/po2 * po2/po1 * po1/po
+
+// Results 
+printf("\n Exit to reservoir pressure ratio is %.3f", pe_by_po)
+