calculate takeoff distance in matlab

To calculate the required takeoff distance of an aircraft in Matlab, we need to first define the relevant parameters. Assuming that we have already defined these values, we can then use the following formula:

main.m
TOD = (V^2/(2*g))*(mu*(W-CLmax*0.5*rho*V^2*S) - T)
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where:

• TOD = takeoff distance [m]
• V = takeoff speed [m/s]
• g = acceleration due to gravity [9.81 m/s^2]
• mu = coefficient of friction between the runway surface and the tires (usually taken as 0.03 for dry pavement)
• W = weight of the aircraft [N]
• CLmax = maximum lift coefficient of the aircraft (usually provided by the manufacturer)
• rho = air density [kg/m^3]
• S = wing area [m^2]
• T = thrust of the aircraft [N]

Here's an example implementation in Matlab:

main.m
% Define parameters
V = 70;         % m/s
g = 9.81;       % m/s^2
mu = 0.03;
W = 50000;      % N
CLmax = 1.5;
rho = 1.225;    % kg/m^3
S = 80;         % m^2
T = 80000;      % N

% Calculate takeoff distance
TOD = (V^2/(2*g))*(mu*(W-CLmax*0.5*rho*V^2*S) - T)
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This will output the required takeoff distance, in meters, for the given set of parameters.