calculate lift and drag of airplane at different velocity in matlab

main.m
% Constants
S = 30; % Wing area in square meters
Cd0 = 0.02; % Coefficient of drag at zero lift
K = 0.04; % Lift-induced drag factor
Cl_max = 1.2; % Maximum coefficient of lift
rho = 1.225; % Air density in kg/m^3
V = 100:5:300; % Range of velocities in m/s

% Calculating Lift and Drag
CL = Cl_max;
CD = Cd0 + K * CL.^2;

lift = 0.5 * rho * V.^2 * S * CL;
drag = 0.5 * rho * V.^2 * S * CD;

% Plotting
figure;
subplot(2,1,1);
plot(V, lift);
xlabel('Velocity (m/s)');
ylabel('Lift (N)');
title('Lift vs Velocity');

subplot(2,1,2);
plot(V, drag);
xlabel('Velocity (m/s)');
ylabel('Drag (N)');
title('Drag vs Velocity');
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