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+clc
+// Example 5.7.py
+// Consider the wind tunnel described in example 5.2. Estimate the ratio of diffuser
+// throat area to nozzle throat area required to allow the tunnel to start. Also, 
+// assuming that the diffuser efficiency is 1.2 after the tunnel has started, calculate
+// the pressure ratio across the tunnel necessary for running i.e. calculate the ratio
+// of total pressure at the diffuser exit to the reservoir pressure.
+
+// Variable declaration
+
+M = 2.5      // mach number before the shock
+eta_d = 1.2  // diffuser efficiency
+
+// Calculations
+
+// from table for M = 2.5
+po2_by_po1 = 0.499              // po2/po1
+At2_by_At1 = 1 / po2_by_po1     // At2/At1 = po1/po2
+ 
+Pdo_by_po = eta_d * po2_by_po1  // pdo/po
+
+// Results
+printf("\n Ratio of diffuser throat area to nozzle throat area %.2f", At2_by_At1)
+
+printf("\n Ratio of total pressure at the diffuser exit to the reservoir pressure, %.3f",(Pdo_by_po))
+