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diff --git a/2126/CH4/EX4.3/3.sce b/2126/CH4/EX4.3/3.sce
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+clc
+clear
+
+//input data
+M1=2 //Mach number at entry
+P1=1.4 //Static Pressure at entry in bar
+T1=323 //Static Temperature at entry in K
+Cp=1.005 //Specific heat of dry air in kJ/kg-K
+k=1.4 //Adiabatic constant
+R=287 //Gas constant in J/kg-K
+
+//calculation
+t1=0.555 //Temperature ratio at entry from gas tables (M=2,k=1.4,isentropic)
+To1=T1/t1 //Total stagnation temperature at inlet in K
+p1=0.364 //Pressure ratio  at entry from gas tables (M=2,k=1.4,isentropic)
+Po1=P1/p1 //Stagnation Pressure at entry in bar
+t2=0.529 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=2) 
+Tt=T1/t2 //Static critical temperature in K
+t3=0.793 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=2)
+Tot=To1/t3 //Stagnation critical temperature in K
+To2=Tot //Stagnation exit temperation in K
+q=Cp*(To2-To1) //The heat transferred per unit mass flow in kJ/kg
+a1=sqrt(k*R*T1) //Sound velocity in m/s
+C1=M1*a1 //Air velocity in m/s
+d1=(P1*10^5)/(R*T1) //density of air in kg/m^3
+ma=d1*C1 //Mass flow rate per unit area in kg/s-m^3
+
+//output
+printf('(A)Mass flow rate per unit area is %3.2f kg/s-m^2\n (B)Final temperarure is %3.3f K\n (C)Heat added is %3.2f kJ/kg',ma,Tt,q)