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+clc; funcprot(0);
+//Example 15.7 Thrust Horsepower of a constant speed propeller at an altitude
+// Initialisation of variables
+V = 125*1.467;      // Velocity in ft/sec
+n = 1800/60;        // Rotaion per second
+D = 9.5;              // Diameter in ft
+P = 600*550;
+rho = 0.001756;
+
+// Calculations
+//For Beta = 23 degree
+Cp = P/(rho*n^3*D^5);
+ThrustCoeff = rho*n^2*D^4;
+VeloCoeff = n*60*D/88;
+
+VBynD = [1 0.9 0.8 0.7 0.6];
+Ct = [0.073 0.081 0.087 0.096 0.108];              // From figure 15.4 for corrospondiong values of V/nD at Cp = 0.066
+T = Ct*ThrustCoeff;
+V = VBynD*VeloCoeff;
+
+Result = zeros(5,6);
+Result(:,1) = VBynD';
+Result(:,2) = Ct';
+Result(:,3) = Result(:,2)/Cp;
+Result(:,4) = diag(diag(Result(:,3))*diag(Result(:,1)));        // Using equation 15.5.5
+Result(:,5) = Result(:,4)*P/550;
+Result(:,6) = V';
+//Results 
+
+disp(Result,"!! V/nD   Ct        Ct/Cp        Efficiency   thp          V(mph)  !!") ;