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+clc
+// Example 4.9.py
+// Consider the arrangement shows in fig. 4.29. A 15 degree half angle diamond 
+// wedge airfoil is in supersonic flow at zero angle of attack. A pitot tube is
+// inserted into the flow at the location shown in fig 4.29. The pressure measured
+// by the Pitot tube is 2.596 atm. At point a on the backface, the pressure is 0.1
+// atm. Calculate the freestream Mach number M1.
+
+//
+
+// Variable declaration
+theta = 15.0    // wedge angle/deflection (in degrees)
+po4 = 2.596     // measured pressure (in atm)
+p3 = 0.1        // pressure at point a (in atm)
+
+// Calculations 
+
+po4_by_p3 = po4/p3
+
+// from Table A 2 for po4/p3  = 25.96
+M3 = 4.45
+v3 = 71.27
+v2 = v3 - 2*theta
+
+// from Table A 5, for v2 = 41.27 degrees
+M2 = 2.6
+// Mn2 = M2*sin((beta1-theta)*%pi/180)  @equation 1
+
+// Guessing
+
+// Guess 1
+M1 = 4.0                          // Guess for freestream number
+beta1 = 27.0                       // from fig 4.5 (in degrees)
+Mn1 = M1*sin(beta1*%pi/180)         // mach number normal to shock
+
+// from Table A2 for Mn1 = 1.816
+Mn2 = 0.612                     
+// but Mn2 from equation 1 is 0.54
+
+// Guess 2
+M1 = 4.5                          // Guess for freestream number
+beta1 = 25.5                       // from fig 4.5 (in degrees)
+Mn1 = M1*sin(beta1*%pi/180)         // mach number normal to shock
+
+// from Table A2 for Mn1 = 1.937
+Mn2 = 0.588                     
+// but Mn2 from equation 1 is 0.47
+
+// Guess 3
+M1 = 3.5                          // Guess for freestream number
+beta1 = 29.2                       // from fig 4.5 (in degrees)
+Mn1 = M1*sin(beta1*%pi/180)         // mach number normal to shock
+
+// from Table A2 for Mn1 = 1.71
+Mn2 = 0.638                     
+// but Mn2 from equation 1 is 0.638
+
+
+
+
+// Result 
+printf("\n Freestream mach number is %.1f", M1)
+