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+clc; funcprot(0);
+//Example 8.2  Lift Equation
+
+// Initialisation of variables
+V = 90*1.467;        // Velocity in ft/s
+S = 300;            //Wing Area.
+rho = 0.00237;
+W = 3000;
+
+// Calculations
+Cl = W*2/(rho*S*V^2);            // From figure 8.8
+
+//Results 
+disp("Corrosponding value of alpha for the above Lift Coefficient is 1.7 degree (from fig 8.8).",Cl,"Lift Coefficient for the above data is :");