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+T1 = 233; V1 = 300; cp = 1.005; g = 1.4;
+T2 = T1+((V1^2)/(2*cp))*1e-03 ;
+P1 = 35;
+P2 = P1*(T2/T1)^(g/(g-1));
+rp = 10; // Pressure ratio
+P3 = rp*P2;
+T3 = T2*(P3/P2)^((g-1)/g);
+T4 = 1373;
+T5 = T4-T3+T2;
+P4 = P3;
+P5 = P4*(T5/T4)^(g/(g-1));
+disp("K",T5,"Temperature at the turbine exit is")
+disp("kPa",P5,"Pressure at the turbine exit is")
+P6 = P1;
+T6 = T5*(P6/P5)^((g-1)/g);
+V6 = (2*cp*1000*(T5-T6))^0.5 ;
+disp("m/s",V6,"Velocity of the gas at the nozzle exit is")
+w = 50;
+Ve = V6; Vi = 300;
+Wp_dot = w*Vi*(Ve-Vi);
+h4 = 1373; h3 = 536.66;
+Q1 = w*cp*(h4-h3); // in kJ/kg
+np = Wp_dot/(Q1*1000);
+disp("%",np*100,"The propulsive efficiency of the cycle is") \ No newline at end of file