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+clc; funcprot(0);
+//Example 8.1 Lift Equation
+
+// Initialisation of variables
+V = 100*1.467; // Velocity in ft/s
+alpha =4;
+S = 250; //Wing Area.
+rho = 0.00237;
+
+// Calculations
+Cl = 0.649; // From figure 8.8
+W = Cl*rho/2*S*V^2;
+
+//Results
+disp(W,"Weight with which an airplane can fly with Clark Y wing (lb) :"); \ No newline at end of file