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diff --git a/3765/CH3/EX3.4/Ex3_4.sce b/3765/CH3/EX3.4/Ex3_4.sce
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+clc
+// Example 3.4.py
+// A normal shock wave is standing in the test section of a supersonic wind tunnel.
+// Upstream of the wave, M1 = 3, p1 = 0.5 atm, and T1 = 200 K. Find M2, p2, T2 and
+// u2 downstream of the wave
+
+
+// Variable declaration from example 1.1
+M1 = 3.0         // upstream mach number
+p1 = 0.5         // upstream pressure (atm)
+T1 = 200.0       // upstream temperature (K)
+R = 287.0        // gas constant (J/Kg/K)
+gamma1 = 1.4      // ratio of specific heats for air
+
+// Calculations 
+
+// from shock relation (Table A2) for M1 = 3.0
+// subscript 2 means downstream of the shock
+p2_by_p1 = 10.33    // p2/p1
+T2_by_T1 = 2.679    // T2/T1
+M2 = 0.4752         // M2
+
+p2 = p2_by_p1 * p1       // downstream pressure (atm)
+T2 = T2_by_T1 * T1       // downstream temperature (K)
+a2 = (gamma1*R*T2** 0.5) // speed of sound downstream of the shock (m/s)
+u2 = M2*a2               // downstream velocity (m/s)
+
+
+// Result 
+printf("\n M2 = %.4f",(M2))
+
+printf("\n p2 = %.3f atm",(p2))
+
+printf("\n T2 = %.1f K",(T2))
+
+printf("\n u2 = %.1f m/s",(u2))
+