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diff --git a/2223/CH8/EX8.3/Ex8_3.sce b/2223/CH8/EX8.3/Ex8_3.sce
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+// scilab Code Exa 8.3 Calculation on a compressor cascade
+theta=25; // Camber angle
+gamma_a=30; // stagger angle
+i=5; // incidence
+t_c=0.031; // momentum thickness-chord ratio(t/l)
+p_c=1; // pitch-chord ratio
+
+//part(a)cascade blade angles
+beta1=((2*gamma_a)+theta)*0.5; //  blade angle at entry
+beta2=((2*gamma_a)-theta)*0.5; // blade angle at exit
+disp ("(a)therefore, the blade angles are")
+disp ("degree",beta1,"beta1=")
+disp ("degree",beta2,"beta2=")
+
+//part(b) the nominal air angles
+alpha1=beta1+i; // air angle at entry
+alpha2=atand(tand(alpha1)-(1.55/(1+(1.5*p_c)))); // air angle at exit
+disp ("(b)therefore, the air angles are")
+disp ("degree",alpha1,"alpha1=")
+disp ("degree",alpha2,"alpha2=")
+
+//part(c) stagnation pressure loss coefficient
+Y=2*t_c*p_c*(cosd(alpha1)^2)/(cosd(alpha2)^3);
+disp (Y,"(c)the stagnation pressure loss coefficient is")
+
+// part(d)drag coefficient
+alpham=atand(0.5*(tand(alpha1)+tand(alpha2)));
+C_D=p_c*Y*(cosd(alpham)^3)/(cosd(alpha1)^2);
+disp (C_D,"(d)the drag coefficient is")
+
+// part(e)Lift coefficient
+C_L=(2*p_c*(tand(alpha1)-tand(alpha2))*cosd(alpham))-(C_D*tand(alpham));
+disp (C_L,"(e)the Lift coefficient is")