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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 :");
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