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diff --git a/3685/CH21/EX21.5/Ex21_5.sce b/3685/CH21/EX21.5/Ex21_5.sce
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+clc
+// Given that
+v = 850 // Speed of turbojet in km/h
+m = 50 // Air mass flow rate in kg/s
+s = 200 // Entropy drop across the nozzle in kJ/kg
+n_n = 0.9 // Nozzle efficiency
+r = 80 // Air fuel ratio
+cv = 40 // Heating value of fuel in MJ/kg
+Cp = 1005 // Heat capacity of air in J/kgK
+printf("\n Example 21.5\n")
+Vo = v*(5/18)
+m_f = m/r
+Ve = sqrt(2*Cp*s*n_n)
+T = (m+m_f)*Ve-m*Vo
+TP = T*Vo
+PP = (1/2)*(m+m_f)*(Ve^2)-(1/2)*(m*Vo^2)
+n_p = TP/PP
+n_t = PP/(m_f*cv*1000000)
+n = n_t*n_p
+printf("\n Propulsive power = %f MW,\n Thrust power = %f kW,\n Propulsive efficiency = %f percent\n Thermal efficiency = %f percent,\n Overall efficiency = %f percent ",PP*(10^-6),TP*(10^-3),n_p*100,n_t*100,n*100)
+
+
+
+