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+clc
+// Given that
+p1 = 8 // Pressure of entrance in bar
+t1 = 1125 // Temperature of entrance in K
+p2 = 1.5 // Pressure of exit in bar
+n = 11 // No of stages
+Vf = 110 // Axial velocity of flow in m/s
+n_p = 0.85 // Polytropic efficiency 
+Vb = 140 // Mean velocity in m/s
+gama = 1.33 // Heat capacity ratio for gases
+Cp = 1.15 // Heat capacity of gases in kJ/kgK
+r = 0.5 // Fraction of reaction
+printf("\n Example 21.3\n")
+t2 = t1*((p2/p1)^((gama-1)*n_p/gama))
+t2_s = t1*((p2/p1)^((gama-1)/gama))
+n_s = (t1-t2)/(t1-t2_s)
+Wt = Cp*(t1-t2)
+Wt_s = Wt/n
+V_w1 = (((Wt_s*1000)/Vb) + Vb)/2
+alpha1 = atand(Vf/V_w1)
+alpha2 = alpha1
+beta1 = atand(Vf/(V_w1-Vb))
+h_s = Wt_s
+t_s = h_s/Cp
+t1_ = t1-t_s
+t1_s = t1*((t1_/t1)^(gama/((gama-1)*n_p)))^((gama-1)/gama)
+n_st = (t1-t1_)/(t1-t1_s)
+printf("\n The blade angle at the inlet = %f degree,and at the exit = %f degree,\n The overall efficiency of the turbine = %f percent\n The stage efficiency = %f percent",alpha1,beta1,n_s*100,n_st*100)
+// The answers given in the book contain round off error.
+
+
+
+