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diff --git a/689/CH15/EX15.4/4.sce b/689/CH15/EX15.4/4.sce
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+clc; funcprot(0);
+//Example 15.4 Thrust Horse Power for 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 0.8 0.7 0.6 0.5 0.4 ];
+Ct = [Ct0 0.082 0.100 0.120 0.132 0.144 ];
+Cp = [Cp0 0.080 0.093 0.103 0.108 0.112 ];
+CtByCp = diag(Ct)/diag(Cp);
+T = T0*(Cp0/Ct0)*CtByCp;
+Eff = diag(V)*diag(CtByCp);
+Eff0 = Eff(1);
+RPM = Eff/Eff0*2200;
+Cp0 = linspace(Cp0,Cp0, 6);
+Cp0ByCp = diag(diag(Cp0)/diag(Cp))
+
+Eff/Eff0;
+Eff/Eff0*(n*60);
+bhp = [125 123 117 112 110 109];        // From manufactures chart
+thp = diag(bhp)*diag(Eff);
+sigma = 0.7384;                         // From table 4.1;
+Bhp10KBySL = 0.673;                     // Ratios of BHP from fig 14.3
+RPMfactor = Bhp10KBySL/sigma;
+BHPfactor = RPMfactor*Bhp10KBySL;
+
+Result = zeros(6,9);
+Result(:,1) = V';
+Result(:,2) = RPM;
+Result(:,3) = bhp';
+Result(:,4) = diag(diag(Result(:,1))*diag(Result(:,2))*(D/88));
+Result(:,5) = Eff;
+Result(:,6) = RPM*RPMfactor;
+Result(:,7) = bhp'*BHPfactor;
+Result(:,8) = Result(:,4)*RPMfactor;
+Result(:,9) = diag(diag(Result(:,7))*diag(Result(:,5)));
+//Results 
+
+disp(Result,"!! V/nD         rpm_SL       bhp_SL  V_SL         Eff_SL       rpm_10K      bhp_10K      V_10K        thp_10K      !!") ;
+disp("There is a calculation mistake in calculating n/no hence the dependent answer varies");