initial commit / add all books

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diff --git a/2223/CH9/EX9.4/Ex9_4.sav b/2223/CH9/EX9.4/Ex9_4.sav
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+++ b/2223/CH9/EX9.4/Ex9_4.sav
diff --git a/2223/CH9/EX9.4/Ex9_4.sce b/2223/CH9/EX9.4/Ex9_4.sce
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+// scilab Code Exa 9.4 axial turbine stage 3000 rpm 

+

+d=1; // mean diameter of the impeller blade in m

+r=d/2;

+N=3e3; // rotor Speed in RPM

+a_r(1)=1; // aspect ratio

+a_r(2)=2;

+a_r(3)=3;

+alpha2=70; //  air angle at nozzle exit

+alpha3=0;

+beta_2=54; //  air angle at rotor entry

+sigma=0.5*(sind(alpha2)); // blade to gas speed ratio

+u=%pi*d*N/60;

+c2=u/sigma;

+cx=c2*(cosd(alpha2));

+beta_3=beta_2;  //  air angle at rotor exit

+phi=cx/u;

+e_R=beta_2+beta_3; // Rotor deflection angle

+zeeta_p_N=0.025*(1+((alpha2/90)^2)); // profile loss coefficient for nozzle

+zeeta_p_R=0.025*(1+((e_R/90)^2)); // profile loss coefficient for rotor

+for i=1:3

+disp(a_r(i),"when Aspect ratio=")

+zeeta_N=(1+(3.2/a_r(i)))*zeeta_p_N; // total loss coefficient for nozzle

+zeeta_R=(1+(3.2/a_r(i)))*zeeta_p_R; // total loss coefficient for rotor

+a=(zeeta_R*(secd(beta_3)^2))+(zeeta_N*(secd(alpha2)^2));

+b=phi*(tand(alpha2)+tand(beta_3))-1;

+c=(zeeta_R*(secd(beta_3)^2))+(zeeta_N*(secd(alpha2)^2))+(secd(alpha3)^2);

+n_tt=inv(1+(0.5*(phi^2)*(a/b)));

+disp("%",n_tt*1e2,"total-to-total efficiency is")

+n_ts=inv(1+(0.5*(phi^2)*(c/b)));

+disp("%",n_ts*1e2,"total-to-static efficiency is")

+end