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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) :");
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