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+clc; funcprot(0);
+//Example 8.10  Polar Curves
+
+// Initialisation of variables
+W = 2000;
+S = 180;
+V = 120*1.467;
+rho = 0.002378;
+
+// Calculations
+Cl = 2*(W/S)/(rho*V^2);
+Cd = 0.019 ;     //From fig 8.19
+LbyD = Cl/Cd;
+L = W;         // for level flight lift = weight
+D = L/LbyD;
+HP = D*V/550;
+
+//Results 
+disp(HP,"Horse power required to move the wing forward(hp) :");
+\ No newline at end of file