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..