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+clc
+// Example 3.6.py
+// Consider a point in a supersonic flow where the static pressure is 0.4 atm. When
+// a pitot tube is inserted in the at this point, the pressure measured by the
+// pitot tube is 3 atm. Calculate the mach number at this point.
+
+// Variable declaration
+p1 = 0.4 // static pressure (in atm)
+po2 = 3.0 // pressure measured by the pitot tube (in atm)
+
+//Calculations
+// from table A2 for po2/p1 = 7.5
+M1 = 2.35
+
+// Results
+printf("\n Mach number is %.2f",(M1))
+