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+clc;
+clear;
+A=1*(10^(-4));//m^2
+p1=80;//kPa(abs)
+p2=40;//kPa(abs)
+p0=101;//kPa(abs)
+pcritical=0.528*p0;//kPa(abs)
+k=1.4;
+//for (a) pth=p1>pcritical
+Math1=((((p0/p1)^((k-1)/k))-1)/((k-1)/2))^0.5;//Math=Mach number at throat
+//dth/d0=p1/p0; dth=density at throat
+dth1=(1.23)*(1/(1+(((k-1)/2)*(Math1^2))))^(1/(k-1));//kg/(m^3); density at throat
+Tth1=(288)*(1/(1+(((k-1)/2)*(Math1^2))));//K; temperature at throat
+Vth1=Math1*(286.9*Tth1*k)^0.5;//m/sec
+m1=dth1*A*Vth1;//kg/sec
+disp("kg/sec",m1,"a) The mass flowrate through the duct=")
+//for (b) pth=p2<pcritical, hence
+Math2=1;
+dth2=1.23*(1/(1+(((k-1)/2)*(Math2^2))))^(1/(k-1));//kg/(m^3); density at throat
+Tth2=(288)*(1/(1+(((k-1)/2)*(Math2^2))));//K; temperature at throat
+Vth2=Math2*(286.9*Tth2*k)^0.5;//m/sec
+m2=dth2*A*Vth2;//kg/sec
+disp("kg/sec",m2,"b) The mass flowrate through the duct=") \ No newline at end of file