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+clc
+// Example 5.2.py
+// A supersonic wind tunnel is designed to produce Mach 2.5 flow in the test section
+// with standard sea level conditions. Calculate the exit area ratio and reservoir
+// conditions necessary to achieve these design conditions.
+
+// Variable declaration
+Me = 2.5          // exit mach number
+pe = 1.0          // sea level pressure (in atm)
+Te = 288.0        // sea level temperature (in K) 
+// Calculations
+
+// from table A1 for Me = 2.5
+Ae_by_Astar = 2.637        // Ae/Astar
+po_by_pe = 17.09           // po/p 
+To_by_Te = 2.25            // To/T 
+
+po = po_by_pe * pe         // reservoir pressure (in atm)
+To = To_by_Te * Te         // reservoir temperature (in K)
+
+// Results
+printf("\n Area ratio required %.3f", Ae_by_Astar)
+
+printf("\n Reservoir pressure required %.2f atm", po)
+
+printf("\n Reservoir temperature required %.1f K", To)
+