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+clc; funcprot(0);
+//Example 15.2 Thrust of a fixed pitch propeller
+// Initialisation of variables
+V = 125*1.467;      // Velocity in ft/sec
+n = 2200/60;        // Rotaion per second
+D = 6;              // Diameter in ft
+rho = 0.002378;
+
+// Calculations
+//For Beta = 23 degree
+VnD0 = V/(n*D);
+Ct0 = 0.075;
+Cp0 = 0.076;
+T0 = Ct0*rho*n^2*D^4;
+
+V = [VnD0 0.6 0.5 0.4 0.3 0.2 0.1 0];
+Ct = [Ct0 0.120 0.132 0.144 0.160 0.173 0.186 0.198];
+Cp = [Cp0 0.103 0.108 0.112 0.118 0.122 0.124 0.127];
+CtByCp = diag(Ct)/diag(Cp);
+T = T0*(Cp0/Ct0)*CtByCp;
+Eff = diag(V)*diag(CtByCp);
+Result = zeros(8,6);
+Result(:,1) = V';
+Result(:,2) = Ct';
+Result(:,3) = Cp';
+Result(:,4) = diag(CtByCp);
+Result(:,5) = diag(T);
+Result(:,6) = Eff;
+
+//Results 
+
+disp(Result,"!!  V/nD        Ct       Cp       Ct/Cp        T            Efficiency   !!") ;