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diff --git a/3511/CH6/EX6.15/Ex6_15.sce b/3511/CH6/EX6.15/Ex6_15.sce
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+clc;
+p01=1; // Stagnation pressure at entry in bar
+pa=0.93; // Static pressure at entry in bar
+T1=10+273;// Static temperature in entry in kelvin
+p02=6; // Pressure at state 2 in bar
+T02=230+273; // Temperature at state 2 in kelvin
+P=5100; // Turbine output power in kW
+A=0.1; // Compressor entry area in m^2
+Cpa=1.005;// Specific heat of air  at constant pressure in kJ/kg K
+Cpg=1.147;// Specific heat of fuel at constant pressure in kJ/kg K
+rg=1.33;// Specific heat ratio of fuel
+r=1.4; // Specific heat ratio of air
+R=287; // Characteristic constant in J/kg K
+T04=460+273; // Exhaust pipe temperature in kelvin
+
+M=sqrt (((p01/pa)^((r-1)/r)-1)/((r-1)/2));
+T01=T1*(1+(r-1)/2*M^2);
+T_02=T01*(p02/p01)^((r-1)/r);
+eff_c=(T_02-T01)/(T02-T01);
+row_s=(pa*10^5)/(R*T1);
+a=sqrt (r*R*T1);
+V=M*a;
+m=row_s*A*V;
+T03=(P/(m*Cpg))+T04;
+
+disp ("%",eff_c*100,"Compressor efficiency = ");
+disp ("kg/s",m,"Mass flow rate = ");
+disp ("K   (roundoff error)",T03,"Turbine inlet stagnation temperature = ");