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clc; funcprot(0);
//Example 15.5 Thrust of a constant speed propeller
// Initialisation of variables
V = 125*1.467; // Velocity in ft/sec
n = 1800/60; // Rotaion per second
D = 9.5; // Diameter in ft
P = 600*550;
rho = 0.002378;
// Calculations
//For Beta = 23 degree
Cp = P/(rho*n^3*D^5);
ThrustCoeff = rho*n^2*D^4;
VeloCoeff = n*60*D/88;
5
VBynD = linspace(0.5,0,6);
Ct = [0.09 0.101 0.112 0.122 0.132 0.142]; // From figure 15.4 for corrospondiong values of V/nD at Cp = 0.066
T = Ct*ThrustCoeff;
V = VBynD*VeloCoeff;
Result = zeros(6,4);
Result(:,1) = VBynD';
Result(:,2) = Ct';
Result(:,3) = T';
Result(:,4) = V';
//Results
disp(Result,"!! V/nD Ct T V(mph) !!") ;
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