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diff --git a/1358/CH7/EX7.7/Example77.sce b/1358/CH7/EX7.7/Example77.sce
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+// Display mode
+mode(0);
+// Display warning for floating point exception
+ieee(1);
+clear;
+clc;
+disp("Turbomachinery Design and Theory,Rama S. R. Gorla and Aijaz A. Khan, Chapter 7, Example 7")
+Cpg = 1147;
+disp("Temperature Drop = T01 -T03")
+Drop = 145;
+U = 345;
+psi = Cpg*(Drop)/U^2
+disp("Using velocity diagram")
+disp("U/Ca = tan(beta3) - tan(alpha3)")
+disp("tan(beta3) = 1/phi + tan(alpha3)")
+alpha3 = 12;
+phi = 0.75;
+beta3 = atan(1/phi + tan(alpha3*%pi/180))*180/%pi
+disp("Psi = phi*(tan(beta2) +tan(beta3))")
+disp("DOR = phi/2 *(tan(beta3) - tan(beta2))")
+disp("tan(beta3) = (psi + 2*DOR)/(2*phi)")
+DOR = (tan(beta3*%pi/180) *2*phi - psi)/2 *100
+disp("tan(beta2) = (psi-2*DOR)/(2*phi)")
+beta2 = atan((psi-2*DOR/100)/(2*phi))*180/%pi
+alpha2 = atan(tan(beta2*%pi/180)+(1/phi))*180/%pi
+Ca1 = U*phi//m/s
+C2 = Ca1/cos(alpha2*%pi/180)//m/s
+disp("R2 = T02-T2 = C2^2 /2Cp")
+R2 = C2^2 /(2*Cpg)
+disp("R3 = T2-T2s = Tn*C2^2/(2Cpg)")
+Tn = 0.05;
+R3 = Tn*C2^2 /(2*Cpg)
+T2 = 1100-R2//K
+T2s = T2 - R3//K
+P01 = 4;//bars
+T01 = 1100;
+P2 = P01*(T2s/T01)^4
+R = 0.287;
+rho2 = P2*100/(R*T2)//kg/m3
+disp("Nozzle Throat area in A in m2")
+C1 = C2;//m/s
+rho1 = 0.907;//kg/m3
+m = 24;
+A = m/(rho1*C1)
+A1 = m/(rho1*Ca1)