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+//Chapter-4, Illustration 1, Page 161
+//Title: Steam Nozzles and Steam Turbines
+//=============================================================================
+clc
+clear
+
+//INPUT DATA
+P1=3.5;//Pressure at entry in MN/(m^2)
+T1=773;//Temperature at entry in K
+P2=0.7;//Pressure at exit in MN/(m^2)
+ma=1.3;//mass flow rate of air in kg/s
+y=1.4;//Ratio of specific heats
+R=0.287;//Universal gas constant in KJ/Kg-K
+
+//CALCULATIONS
+c=y/(y-1);//Ratio
+Pt=((2/(y+1))^c)*P1;//Throat pressure in MN/(m^2)
+v1=(R*T1)/(P1*1000);//Specific volume at entry in (m^3)/kg
+Ct=((2*c*P1*v1*(1-((Pt/P1)^(1/c))))^0.5)*1000;//Velocity at throat in m/s
+vt=v1*((P1/Pt)^(1/y));//Specific volume at throat in (m^3)/kg
+At=((ma*vt)/Ct)*(10^6);//Area of throat in (mm^2)
+C2=((2*c*P1*v1*(1-((P2/P1)^(1/c))))^0.5)*1000;//Velocity at exit in m/s
+v2=v1*((P1/P2)^(1/y));//Specific volume at exit in (m^3)/kg
+A2=((ma*v2)/C2)*(10^6);//Area of exit in (mm^2)
+M=C2/Ct;//Mach number at exit
+
+//OUTPUT
+mprintf('Throat area is %3.0f (mm^2) \n Exit area is %3.0f (mm^2) \n Mach number at exit is %3.2f',At,A2,M)
+
+
+
+
+
+
+//==============================END OF PROGRAM=================================