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diff --git a/2223/CH12/EX12.1/Ex12_1.sav b/2223/CH12/EX12.1/Ex12_1.sav
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+// scilab Code Exa 12.1 Calculation on a centrifugal compressor stage 

+T01=335;  // in Kelvin

+funcprot(0);

+p01=1.02; //  Initial Pressure in bar

+dh=0.10; // hub diameter in m

+dt=0.25; // tip diameter in m

+m=5; //  in kg/s

+gamma=1.4;

+N=7.2e3; // rotor Speed in RPM

+d1=0.5*(dt+dh); // Mean Blade ring diameter

+cp=1005; // Specific Heat at Constant Pressure in J/(kgK)

+A=%pi*((dt^2)-(dh^2))/4;

+R=287;

+// I trial

+ro1=(p01*1e5)/(R*T01);

+cx0=m/(ro1*A);

+T0=T01-((cx0^2)/(2*cp));

+n=(gamma-1)/gamma;

+p1=p01*((T0/T01)^(1/n));

+ro=(p1*1e5)/(R*T0);

+cx=m/(ro*A);

+// II Trial

+cx2=123;

+T1=T01-((cx2^2)/(2*cp));

+p2=p01*((T1/T01)^(1/n));

+ro2=(p2*1e5)/(R*T1);

+cx1=m/(ro2*A);

+u1=%pi*d1*N/60;

+beta1=atand(cx1/u1);

+disp("degree",beta1,"air angle at inducer blade entry beta1=")

+w1=cx1/(sind(beta1));

+a1=sqrt(gamma*R*T1);

+Mw1=w1/a1;

+disp(Mw1,"the Relative Mach number at inducer blade entry Mw1=")

+alpha1=atand(cx1/u1);

+disp("degree",alpha1,"air angle at IGVs exit alpha1=")

+c1=cx1/(sind(alpha1));

+T1_new=T01-((c1^2)/(2*cp));

+a1_new=sqrt(gamma*R*T1_new);

+Mw1_new=cx1/a1_new;

+disp(Mw1_new,"the new value of Relative Mach number Mw1_new=")