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clc; funcprot(0);
//Example 8.10 Polar Curves
// Initialisation of variables
W = 2000;
S = 180;
V = 120*1.467;
rho = 0.002378;
// Calculations
Cl = 2*(W/S)/(rho*V^2);
Cd = 0.019 ; //From fig 8.19
LbyD = Cl/Cd;
L = W; // for level flight lift = weight
D = L/LbyD;
HP = D*V/550;
//Results
disp(HP,"Horse power required to move the wing forward(hp) :");
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