Swept Variables
---------------
V_f_wing : [ 0.1  0.3  0.5 ] [m³] fuel volume in the wing

Optimal Cost
------------
W_f : [ 4.63e+03  6.23e+03  7.36e+03 ] [N]

WARNINGS
--------
Unexpectedly Loose Constraints:
0.5886 >= 0.5775 : V_{f_{avail}} ≥ V_f  (in 1 of 3 solutions)
0.7884 >= 0.7769 : V_{f_{avail}} ≥ V_f  (in 1 of 3 solutions)
0.9585 >= 0.9187 : V_{f_{avail}} ≥ V_f  (in 1 of 3 solutions)

Free Variables
--------------
       (CDA0) : [ 0.05      0.05      0.05     ] [m²]  fuselage drag area
            A : [ 12.4      3.78      2.35     ]       aspect ratio
          C_D : [ 0.0136    0.011     0.0099   ]       drag coefficient
          C_L : [ 0.327     0.162     0.121    ]       lift coefficient of wing
          C_f : [ 0.00343   0.00284   0.00261  ]       skin friction coefficient
            D : [ 466       774       1e+03    ] [N]   total drag force
          L/D : [ 24.1      14.8      12.2     ]       lift-to-drag ratio
           Re : [ 4.64e+06  1.21e+07  1.83e+07 ]       Reynold's number
            S : [ 22        29.7      35.6     ] [m²]  total wing area
   T_{flight} : [ 16.6      13.4      12.3     ] [h]   flight time
            V : [ 50.3      62.1      67.9     ] [m/s] cruising speed
          V_f : [ 0.577     0.777     0.919    ] [m³]  fuel volume
V_{f_{avail}} : [ 0.589     0.788     0.958    ] [m³]  fuel volume available
            W : [ 1.35e+04  1.45e+04  1.59e+04 ] [N]   total aircraft weight
          W_f : [ 4.63e+03  6.23e+03  7.36e+03 ] [N]   fuel weight
          W_w : [ 2.65e+03  2.05e+03  2.29e+03 ] [N]   wing weight
     W_w_strc : [ 1.33e+03  269       151      ] [N]   wing structural weight
     W_w_surf : [ 1.32e+03  1.78e+03  2.14e+03 ] [N]   wing skin weight
