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+clc;funcprot(0);//EXAMPLE 11.9

+// Initialisation of Variables

+da=0.018;..........................//Throat Diameter in m

+df=0.0012;......................//Diameter of fuel orifice in m

+Cda=0.82;.................//Coefficient of air flow

+Cdf=0.65;......................//Coefficient of fuel flow

+z=0.006;........................//Level of petrol surface below the throat

+rhoa=1.2;.......................//density of air in kg/m^3

+rhof=750;.........................//density of fuel in kg/m^3

+g=9.81;........................//Acceleration due to gravity in m/s^2

+delp=0.065*10^5;...................//Pressure drop in N/m^2

+//Calculations

+afr1=(Cda/Cdf)*((da/df)^2)*sqrt(rhoa/rhof);..................//Air fuel ratio when the nozzle lip is neglected

+disp(afr1,"Air fuel ratio when the nozzle lip is neglected:")

+afr2=afr1*sqrt(delp/(delp-(g*z*rhof)));.....................//Air fuel ratio when nozzle lip is taken into account

+disp(afr2,"Air fuel ratio when nozzle lip is taken into account:")

+C2=sqrt((2*g*z*rhof)/rhoa);.........................//Minimum velocity of air in m/s

+disp(C2,"Minimum velocity of air (in m/s):")