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 Solution 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..

1. 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

2. Solution
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.