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+clc; funcprot(0);
+//Example 8.5  Flying Level at Altitude 
+
+// Initialisation of variables
+W = 2000;
+S = 350;
+V = 100*1.467;
+rho = 0.002378;
+
+// Calculations
+Cl = 2*(W/S)/(rho*V^2);
+alpha = -1.75;     // From fig 8.15
+Cd = 0.014;        // From fig 8.15
+D = Cd*(rho/2)*S*V^2;
+HP = D*V/550;
+
+// At 10000 ft altitude density is lower as compared to the density at sea level.
+rhoX = 0.001756;
+Cl = 2*(W/S)/(rhoX*V^2);
+alpha = -0.75;     // From fig 8.15
+Cd = 0.016;        // From fig 8.15
+D1 =  Cd*(rhoX/2)*S*V^2;
+HP1 = D1*V/550;
+
+//Results 
+disp(HP1,"Horse power required to move the wing forward(hp) :",D1,"Drag (lb):","!------Part (b)------!",HP,"Horse power required to move the wing forward(hp) :",D,"Drag (lb):","!------Part (a)------!");
+\ No newline at end of file