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diff --git a/689/CH16/EX16.2/2.sce b/689/CH16/EX16.2/2.sce
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+clc; funcprot(0);
+//Example 16.2 Horsepower required at sea level
+// Initialisation of variables
+W = 4225;
+b1 = 38;
+b2 = 35;
+Gap = 5.35;
+S1 = 214;
+S2 = 150;
+Dp = 9.4;           // Parasite drag equivalent
+
+// Calculations
+mu =b2/b1;
+Gab_MeanSpan = 2*Gap/(b1+b2);
+S = S1 + S2;
+sigma = 0.56;                   //From fig 10.10
+r = S2/S1;
+K = mu*(1+r)/sqrt(mu^2 + 2*sigma*r*mu + r^2);
+EMAR = K^2*b1^2/S;
+Coeff_Cdi = 1/(%pi*EMAR);
+Cdp = 1.28*Dp/S;
+Coeff_Cl = W/(0.00256*S)
+Coeff_HPTot = 0.00256*S/375;
+
+V = [54 60 70 80 90 100 110 120 130 140 150];
+Cl = Coeff_Cl*diag(inv(diag(V^2)));
+Cd0 = [0.043 0.019 0.013 0.011 0.010 0.010 0.010 0.009 0.009 0.009 0.009]
+Cdi = Cl^2*Coeff_Cdi;
+Cd = Cd0+Cdi'+Cdp;
+Hp = Coeff_HPTot*diag(diag(V^3)*diag(Cd));
+Result = zeros(11,6);
+Result(:,1) = V';
+Result(:,2) = Cl;
+Result(:,3) = Cd0';
+Result(:,4) = Cdi;
+Result(:,5) = Cd';
+Result(:,6) = Hp;
+
+disp(Result,"!! V       Cl           Cd0      Cdi          Cd           HP Req   !!") ;
+clf();
+plot2d(Result(:,1),Result(:,6));
+xlabel("Miles Per Hour");
+ylabel("HorsePower");
+title("Horsepower required for various airspeeds ");
+set(gca(),"grid",[1 1])
+