Having this how can i output the value for each of my unknowns function F_out =

Question

Having this how can i output the value for each of my unknowns

function F_out = sys_fun(F_in)

T = F_in(1);
L_w = F_in(2);
L_h = F_in(3);
D = F_in(4);
alpha = F_in(5);

% for gamma = 0 , 10 deg, and -3 deg

gamma = 10*(pi/180) ;

W = 410000 ; % N
V = 250 ;    % m/s
rho = 0.228 ;% kg/m^3
C_d0 = 0.02 ;
a_w = 4.8 ;
S = 119 ;    % m^2
K = 1.08 ;
l_w = 0.25 ; % m
l_h = 15 ;   % m
h_t = 0.5 ; % m

f1 = T*cos(alpha)-W*sin(gamma)-D ;
f2 = -T*sin(alpha)+W*cos(gamma)-L_w-L_h ;
f3 = -l_w*L_w-l_h*L_h-h_t*T ;
f4 = L_w -(0.5*rho*(V^2)*a_w*alpha);
f5 = 0.5*rho*(V^2)*S*(C_d0+(K*(alpha^2)));

F_all = [f1;f2;f3;f4;f5] ;

F_out = max(F_all);

end

3. The figure shows the forces acting on an aircraft flying in steady fight (no acceleration). t LH The steady flight (or trim) equations can be expressed ina coordinate system aligned with the flight path as (3) (4) Tsin a W cos L Mi (5) Note that T is not shown in the figure, but it represents the vertical distance between the center of gravity (the origin of the coordinates) and the thrust vector. In these equations, TE thrust E aircraft weight De aircraft drag Lwy E wing lift LH horizontal tail lift Y flight-path angle a E aircraft angle of attack First, we must determine what is unknown. The unknown quantities depend on the problem to be solved, but a typical situation may be that the aircraft properties are known and a certain flight

Explanation / Answer

Since from the matlab code, it seems you had calculated the values as f1, f2, f3, f4, f5 , you can use the disp() function to print the value.

Eg:

disp(f1); it will display the value of f1 variable.

use the disp function after the value of the vaariable is calculated according to your equation in the program.

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