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+// scilab Code Exa 13.1 ninety degree IFR turbine
+t=650; // in degree C
+T01=t+273; // in Kelvin
+p3=1; //  Exit Pressure in bar
+gamma=1.4;
+sigma=0.66; // blade-to-isentropic speed ratio
+N=16e3; // rotor Speed in RPM
+b2=5/100; // blade height at entry in m
+alpha_2=20;  //  air angle at nozzle exit
+d_r=0.45; // rotor diameter ratio(d3/d2)
+p01_3=3.5; // total-to-static Pressure Ratio(p01/p3) 
+n_N=0.95; // Nozzle Efficiency 
+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)
+R=287;
+n=(gamma-1)/gamma;
+
+// part(a) the rotor diameter
+c_0=sqrt(2*cp*T01*(1-(p01_3^(-n))))
+u_2=sigma*c_0;
+d2=60*u_2/(%pi*N);
+disp("cm",d2*1e2,"(a)the rotor diameter is")
+
+// part(b) air angle at rotor blade exit
+d3=d2*d_r;
+c_r2=u_2*tand(alpha_2);
+u3=%pi*d3*N/60;
+beta3=atand(c_r2/u3);
+disp("degree",beta3,"(b) air angle at rotor blade exit beta3=")
+
+// part(c) mass flow rate
+T03=T01-((u_2^2)/cp);
+T3=T03-((c_r2^2)/(2*cp));
+T2=T3+((0.5*(u_2^2))/cp);
+c2=u_2/(cosd(alpha_2));
+p01_2=(1-(((0.5*(c2^2))/(cp*n_N))/T01))^(-1/n);
+p01=p3*p01_3;
+p2=p01/p01_2;
+ro2=(p2*1e5)/(R*T2);
+m=ro2*c_r2*%pi*d2*b2;
+disp("kg/s",m,"(c) mass flow rate is")
+
+// part(d) hub and tip diameters at the rotor exit
+ro3=(p3*1e5)/(R*T3);
+b3=m/(ro3*c_r2*%pi*d3);
+dh=d3-b3;
+disp("cm",dh*1e2,"(d)hub diameter at the rotor exit is")
+dt=d3+b3;
+disp("cm",dt*1e2,"(d)tip diameter at the rotor exit is")
+
+// part(e) Determining the power developed
+P=m*(u_2^2);
+disp ("kW",P/1000,"(e)Power developed is")
+
+// part(f) the total-to-static Efficiency of the stage
+n_ts=(u_2^2)/(cp*T01*(1-((p3/p01)^n)));
+disp("%",n_ts*1e2,"(f)the total-to-static Efficiency of the stage is")