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diff --git a/629/CH12/EX12.11/example12_11.sce b/629/CH12/EX12.11/example12_11.sce
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+clear
+clc
+//Example 12.11 SHOCK WAVE IN LAVAL NOZZLE
+k=1.4;
+AoA=1/2 ;//AoA=(Ao/A)
+AeAo=4; //AeAo=(Ae/Ao)
+//From table A.1, interpolation for A/Ao=2,
+//for supersonic flow
+M1=2.2;
+//for normal shock
+M2=0.547;
+pt21=0.6281; //pt21=(pt2/pt1)
+pt1=1000; //[kPa]
+pt2=pt21*pt1 //[kPa]
+//for subsonic part at M=M2,
+AAv=1.26; //AAv=(A/Av)
+//Exit area ratio
+//Ae/Av=(Ae/Ao)*(Ao/A)*(A/Av)
+AeAv=AeAo*AoA*AAv //AeAv=(Ae/Av)
+//for subsonic flow at A/Ao=(Ae/Av)
+M=0.24; 
+//Exit pressure
+pe=pt2/((1+(k-1)*M^2/2)^(k/(k-1))) //[kPa]
+printf("\n The static pressure at the exit = %.f kPa.\n",pe)
+\ No newline at end of file