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+clc
+// Example 4.1.py
+// A uniform supersonic stream with M1 = 3.0, p1 = 1 atm, T1 = 288 K encounters
+// a compression corner which deflects the stream by an angle theta = 20 deg. 
+// Calculate the shock wave angle, and p2, T2, M2, po2 and To2 behind the shock
+// wave.
+
+
+// Variable declaration
+M1 = 3.0          // upstream mach number
+p1 = 1.0          // upstream pressure (in atm)
+T1 = 288          // upstream temperature (in K)
+theta = 20        // deflection (in degrees)
+
+// Calculations 
+// subscript 2 means behind the shock
+
+// from figure 4.5 from M1 = 3.0, theta = 20.0 deg.
+beta1 = 37.5                 // shock angle (in degress)
+
+// degree to radian conversion is done by multiplying by %pi/180
+//
+Mn1 = M1 * sin(beta1*%pi/180) // upstream mach number normal to the shock
+
+// from Table A2 for Mn1 = 1.826
+p2_by_p1 = 3.723            // p2/p1
+T2_by_T1 = 1.551            // T2/T1
+Mn2 = 0.6108                
+po2_by_po1 = 0.8011         // po2/po1
+
+p2 = p2_by_p1 * p1          // p2 (in atm) = p2/p1 * p1
+T2 = T2_by_T1 * T1          // T2 (in K) = T2/T1 * T1
+
+M2 = Mn2/(sin((beta1-theta)*%pi/180)) // mach number behind the shock
+
+// from A1 for M1 = 3.0
+po1_by_p1 = 36.73
+To1_by_T1 = 2.8
+
+po2 = po2_by_po1 * po1_by_p1 * p1   // po2 (in atm) = po2/po1 * po1/p1 * p1
+To1 =  To1_by_T1 * T1   // To2 (in atm) = To2/To1 * To1/T1 * T1
+To2 = To1_by_T1 * T1   // To2 (in atm) = To2/To1 * To1/T1 * T1
+
+
+// Result 
+printf("\n Shock wave angle %.2f degrees",(beta1))
+
+printf("\n p2 = %.2f atm", p2)
+
+printf("\n T2 = %.2f K", T2)
+
+printf("\n M2 = %.2f ", M2)
+
+printf("\n po2 = %.2f atm", po2)
+
+printf("\n To2 = %.2f K", To2)
+