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+clc;funcprot(0);//EXAMPLE 11.7
+// Initialisation of Variables
+as=6;........................//Air supply in kg/min
+fs=0.45;..........................//Fuel supply in kg/min
+p1=1.013;.......................//Atmospheric pressure in bar
+t1=300;......................//Atmospheric temperature in Kelvin
+rhof=740;......................//Density of fuel in kg/m^3
+C2=92;........................//Air flow velocity in m/s
+Cda=0.8;....................//Velocity co efficient
+Cdf=0.6;.........................//Coefficient of discharge for fuel
+ga=1.4;........................//Degree of freedom of gas
+r=0.75;......................//ratio of pressure drop across venturi and of that of choke
+R=0.287;........................//Gas constant in kJ/kgK
+//Calculations
+ma=as/60;.................................//Air flow in kg/s
+mf=fs/60;.................................//Fuel flow in kg/s
+cp=R*(ga/(ga-1));.......................//Specific heat capacity of air in kJ/kgK
+p2=((1-(((C2/Cda)^2)*(1/(2*cp*1000*t1))))^(ga/(ga-1)))*p1;...................//Throat pressure in bar
+v1=(R*t1*1000)/(p1*10^5);
+v2=v1*(p1/p2)^(1/ga);................//specific volume in m^3/kg
+A2=(ma*v2)/(C2);.................//Throat area in m^2
+d2=sqrt((4*A2)/%pi);................//Throat diameter in m
+disp(d2*100,"Throat diameter (in cm):")
+pdv=p1-p2;..........//Pressure drop at venturi in bar
+pdj=r*pdv;.............//Pressure drop at jet in bar
+Af=((mf/Cdf)*(1/sqrt(2*rhof*pdj*10^5)));.............//Area of orifice in m^2
+df=sqrt((4*Af)/%pi);................//Orifice diameter in m
+disp(df,"Orifice diameter (in cm):")
+
+
+