coefficient of airplane in matlab

main.m
% Define the aerodynamic properties of the airplane
c_L_alpha = 2*pi;
c_D_0 = 0.04;
k = 0.05;
c_D_alpha = 0.3;

% Define the angle of attack range (in degrees)
alpha = linspace(-15, 15);

% Calculate the coefficient of lift (C_L) and coefficient of drag (C_D)
C_L = c_L_alpha * alpha * pi/180;
C_D = c_D_0 + k*C_L.^2 + c_D_alpha*(alpha*pi/180).^2;

% Plot the coefficient of lift and drag
figure
subplot(2,1,1)
plot(alpha, C_L)
xlabel('Angle of Attack (deg)')
ylabel('C_L')
subplot(2,1,2)
plot(alpha, C_D)
xlabel('Angle of Attack (deg)')
ylabel('C_D')
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main.m
C_L = c_L_alpha * alpha
C_D = c_D_0 + k*C_L^2 + c_D_alpha*alpha^2
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