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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")