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+clc;funcprot(0);//EXAMPLE 11.2

+// Initialisation of Variables

+cp=5;.................//Consumption of petrol in kg/h

+afr = 16;...............//Air fuel ratio

+Af=2*10^(-6);..............//Fuel orifice area in m^2

+z=0.005;................//Distance between tip of jet and level of petrol in float chamber in m

+spgrp=0.75;..............//Specific gravity of petrol

+rhow=1000;.................//Density of water in kg/m^3

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

+Cda=0.8;...............//Coefficient of discharge for venturi throat

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

+//Calculations

+mf=cp/3600;.................//Fuel consumed in kg/sec

+delp=(((mf/(Af*Cda))^2)*(1/(2*spgrp*rhow)))+(g*z*spgrp*rhow);

+disp(delp,"Suction at the throat in (N/m^2)")

+ma=mf*afr;................//Air flow rate

+Atsqr=((ma/Cda)^2)*(1/(2*rhoa*delp));....................//Throat area in m^2

+disp(sqrt(Atsqr)*10^4,"Throat area (in cm^2)")