
          ┃┓                 ┓
          ┃┃                 ┃
          ┃┃                 ┃
          ┃┣╸Outbound.W_fuel ┣╸Outbound.AircraftPerf.W╶⎨
          ┃┃ (3,731N)        ┃ (34,888N)
     Cost╺┫┛                 ┛
 (7,105N) ┃┓               ┓           ┓
          ┃┃               ┃           ┃
          ┃┃               ┃           ┣╸W_tilde╶⎨
          ┃┣╸Return.W_fuel ┣╸W_zfw     ┛ (22,549N)
          ┃┃ (3,374N)      ┃ (31,514N) ┣╸Wing.W╶⎨
          ┃┛               ┛           ┛ (8,965N)



     ┃┓         ┓
     ┃┃         ┃
     ┃┃         ┣╸Outbound╶⎨
     ┃┃         ┃
     ┃┃         ┛
     ┃┃         ┓        ┓
     ┃┣╸Mission ┃        ┣╸AircraftPerf╶⎨
     ┃┃         ┣╸Return ┛
     ┃┃         ┛        ┣╸[2 terms]
 UAV╺┫┃         ┣╸SprintCondition╶⎨
     ┃┃         ┣╸R ≥ R_min
     ┃┃         ┣╸Outbound.AircraftPerf.W ≥ W_zfw + Return.W_fuel
     ┃┛         ┣╸Return.AircraftPerf.W ≥ W_zfw
     ┃┓          ┓
     ┃┃          ┃
     ┃┃          ┣╸Wing╶⎨
     ┃┣╸Aircraft ┛
     ┃┃          ┣╸W_tilde ≥ W_fixed + W_pay + Engine.W
     ┃┛          ┣╸W_zfw ≥ W_tilde + Wing.W
     ┃┣╸HeavyLandingCase╶⎨


Optimal Cost
------------
UAV.Mission.Outbound.W_fuel + UAV.Mission.Return.W_fuel : 7105 [N]

Solution
--------
...constants
g : 9.8 [m/s²] (+1.475) gravitational constant

UAV.Aircraft
  W_mto : 3.862e+04 [N]            maximum takeoff weight
W_tilde : 2.255e+04 [N]            non-wing weight (fixed + payload + engine)
  W_zfw : 3.151e+04 [N]            zero fuel weight
...constants
W_fixed : 14.7      [kN] (+0.7782) fixed weight
  W_pay : 4900      [N]  (+0.2594) payload weight
   CDA0 : 0.05      [m²] (+0.1949) fuselage zero-lift drag area

UAV.Aircraft.Engine
      P_max : 1260    [kW]              maximum shaft power
          W : 2949    [N]               engine weight
...constants
    eta_eng : 0.35            (-1.267)  engine efficiency
      eta_v : 0.85            (-1.267)  propeller viscous efficiency
     h_fuel : 42      [MJ/kg] (-1.141)  fuel heating value
W_eng_coeff : 0.03724 [N]     (+0.1561) engine weight fit coefficient
     A_prop : 0.785   [m²]    (-0.1087) propeller disk area

UAV.Aircraft.Wing
              A : 18.1                         aspect ratio
          I_cap : 1.908e-05 [m⁴]               spar cap area moment of inertia per unit chord
         M_rbar : 3.231e+04                    normalized root bending moment
              S : 28.99     [m²]               wing area
              W : 8965      [N]                wing weight
          W_cap : 4347      [N]                spar cap weight
          W_web : 135.2     [N]                shear web weight
             nu : 0.786                        wing taper/shape parameter
              p : 1.9                          wing taper ratio parameter
              q : 1.45                         wing taper ratio parameter 2
          t_cap : 0.004272                     spar cap thickness/chord ratio
          t_web : 0.0005907                    shear web thickness/chord ratio
            tau : 0.15                         airfoil thickness/chord ratio
...constants
              e : 0.95              (-0.5472)  wing spanwise efficiency
         N_lift : 6                 (+0.3559)  wing loading multiplier
         EI_ref : 1         [m⁶·Pa] (+0.3459)  structural normalization stiffness
          W_ref : 1         [N]     (-0.3459)  structural normalization weight
        k_shear : 1         [1/m⁴]  (+0.3459)  structural normalization shear factor
      sigma_max : 250       [MPa]   (-0.3459)  allowable stress, 6061-T6
         f_wadd : 2                 (+0.3331)  wing added weight fraction
       rho_alum : 2700      [kg/m³] (+0.3331)  density of aluminum
         C_Lmax : 1.5               (-0.1803)  maximum C_L, flaps down
              w : 0.5               (-0.02283) wing-box width/chord
            r_h : 0.75              (+0.01005) wing strut taper parameter
sigma_max_shear : 167       [MPa]   (-0.01005) allowable shear stress

UAV.HeavyLandingCase
   V_stall : 38   [m/s]             stall speed
...constants
V_stallmax : 38   [m/s]   (-0.3605) stall speed limit
    rho_sl : 1.23 [kg/m³] (-0.1803) air density, sea level

UAV.Mission
     R : 5e+06 [m]           mission leg range
W_fuel : 7105  [N]           total fuel weight
...constants
 R_min : 5000  [km] (+1.141) minimum range requirement

UAV.Mission.Outbound
W_fuel : 3731   [N]  fuel weight for this leg
 z_bre : 0.1016      Breguet range parameter

UAV.Mission.Outbound.AircraftPerf
 C_D : 0.01292        total drag coefficient
C_Di : 0.005648       induced drag coefficient
   T : 816.1     [N]  thrust force
   W : 3.489e+04 [N]  aircraft weight

UAV.Mission.Outbound.AircraftPerf.PropulsionPerf
   eta_0 : 0.2686   overall propulsive efficiency
   eta_i : 0.9028   ideal propulsive efficiency
eta_prop : 0.7674   propeller efficiency

UAV.Mission.Outbound.AircraftPerf.WingAero
C_Dp : 0.005547    profile drag coefficient
 C_L : 0.5524      wing lift coefficient
  Re : 4.716e+06   Reynolds number

UAV.Mission.Outbound.FlightState
  V : 69.2     [m/s]                flight speed
...constants
 mu : 1.69e-05 [kg/m/s] (+0.01153)  dynamic viscosity
rho : 0.91     [kg/m³]  (-0.005767) air density

UAV.Mission.Return
W_fuel : 3374   [N]  fuel weight for this leg
 z_bre : 0.1017      Breguet range parameter

UAV.Mission.Return.AircraftPerf
 C_D : 0.01293        total drag coefficient
C_Di : 0.005645       induced drag coefficient
   T : 737.9     [N]  thrust force
   W : 3.151e+04 [N]  aircraft weight

UAV.Mission.Return.AircraftPerf.PropulsionPerf
   eta_0 : 0.2686   overall propulsive efficiency
   eta_i : 0.9027   ideal propulsive efficiency
eta_prop : 0.7673   propeller efficiency

UAV.Mission.Return.AircraftPerf.WingAero
C_Dp : 0.00556     profile drag coefficient
 C_L : 0.5522      wing lift coefficient
  Re : 4.483e+06   Reynolds number

UAV.Mission.Return.FlightState
  V : 65.78    [m/s]               flight speed
...constants
 mu : 1.69e-05 [kg/m/s] (+0.01266) dynamic viscosity
rho : 0.91     [kg/m³]  (-0.00633) air density

UAV.Mission.SprintCondition
...constants
V_reqt : 150 [m/s] (+0.3708) sprint speed requirement

UAV.Mission.SprintCondition.AircraftPerf
 C_D : 0.007884       total drag coefficient
C_Di : 0.0002558      induced drag coefficient
   T : 2340      [N]  thrust force
   W : 3.489e+04 [N]  aircraft weight

UAV.Mission.SprintCondition.AircraftPerf.PropulsionPerf
   eta_0 : 0.2785   overall propulsive efficiency
   eta_i : 0.9362   ideal propulsive efficiency
eta_prop : 0.7958   propeller efficiency

UAV.Mission.SprintCondition.AircraftPerf.WingAero
C_Dp : 0.005903    profile drag coefficient
 C_L : 0.1175      wing lift coefficient
  Re : 1.022e+07   Reynolds number

UAV.Mission.SprintCondition.FlightState
  V : 150      [m/s]                 flight speed
...constants
rho : 0.91     [kg/m³]  (+0.1229)    air density
 mu : 1.69e-05 [kg/m/s] (-0.0002408) dynamic viscosity

Most Sensitive Constraints
--------------------------
UAV.Aircraft
+1.194 : W_tilde ≥ W_fixed + W_pay + W
+1.171 : W_zfw ≥ W_tilde + W

UAV.Aircraft.Engine
+0.1561 : W ≥ W_eng_coeff·P_max^0.803

UAV.Aircraft.Wing
+0.7398  : p ≥ 1.9
+0.7118  : 2·q ≥ 1 + p
+0.3687  : 0.423·w·tau²·t_cap ≥ I_cap·k_shear + 0.92·w·tau·t_cap²
+0.3459  : M_rbar ≥ W_tilde·A·p/(24·W_ref)
+0.3459  : N_lift·M_rbar·A·q²·tau·EI_ref/(S·I_cap·sigma_max) ≤ 8
+0.3331  : W/f_wadd ≥ W_cap + W_web
+0.323   : W_cap ≥ 8·rho_alum·g·w·t_cap·S^1.5·nu/(3·A^0.5)
+0.1275  : tau ≤ 0.15
+0.08454 : nu^3.94 ≥ 0.86·p^-2.38 + 0.14·p^0.56
+0.01005 : A·W_tilde·N_lift·q²/(tau·S·t_web·sigma_max_shear) ≤ 12
+0.01005 : W_web ≥ 8·rho_alum·g·r_h·tau·t_web·S^1.5·nu/(3·A^0.5)

UAV.HeavyLandingCase
+0.3605 : V_stall ≤ V_stallmax
+0.1803 : W_mto ≤ 0.5·rho_sl·V_stall²·C_Lmax·S

UAV.Mission
+1.141   : R ≥ R_min
+0.5395  : W ≥ W_zfw + W_fuel
+0.5365  : W ≥ W_zfw
+0.1803  : W_mto ≥ W_zfw + W_fuel
+0.03316 : W_fuel ≥ W_fuel + W_fuel

UAV.Mission.Outbound
+0.5706 : z_bre ≥ g·R·T/(h_fuel·eta_0·W)
+0.5425 : W_fuel/W ≥ z_bre^1 + z_bre²/2 + z_bre³/6 + z_bre⁴/24

UAV.Mission.Outbound.AircraftPerf
+0.6211 : C_D ≥ CDA0/S + C_Dp + C_Di
+0.6211 : T ≥ 0.5·rho·C_D·S·V²
+0.5648 : W ≤ 0.5·rho·C_L·S·V²
+0.2715 : C_Di ≥ C_L²/(π·e·A)

UAV.Mission.Outbound.AircraftPerf.PropulsionPerf
+0.5706 : eta_0 ≤ eta_eng·eta_prop
+0.5706 : eta_prop ≤ eta_i·eta_v
+0.52   : 4·eta_i + T·eta_i²/(0.5·rho·V²·A_prop) ≤ 4

UAV.Mission.Outbound.AircraftPerf.WingAero
+0.136   : 2.56·C_L^5.881/(Re^1.541·tau^3.319·C_Dp^2.617) + 3.82e-09·tau^6.229/(C_L^0.914·Re^1.379·C_Dp^9.57) + 0.00215·Re^0.1441·tau^0.03325/(C_L^0.0079·C_Dp^0.7337) + 1.19e+04·C_L^9.783·tau^1.764/(Re^0.998·C_Dp^0.909) + 6.14e-06·C_L^6.535/(Re^0.995·tau^0.521·C_Dp^5.192) ≤ 1
+0.01153 : Re = rho/mu·V·(S/A)^0.5

UAV.Mission.Return
+0.5709 : z_bre ≥ g·R·T/(h_fuel·eta_0·W)
+0.5428 : W_fuel/W ≥ z_bre^1 + z_bre²/2 + z_bre³/6 + z_bre⁴/24

UAV.Mission.Return.AircraftPerf
+0.6215 : C_D ≥ CDA0/S + C_Dp + C_Di
+0.6215 : T ≥ 0.5·rho·C_D·S·V²
+0.5645 : W ≤ 0.5·rho·C_L·S·V²
+0.2714 : C_Di ≥ C_L²/(π·e·A)

UAV.Mission.Return.AircraftPerf.PropulsionPerf
+0.5709 : eta_0 ≤ eta_eng·eta_prop
+0.5709 : eta_prop ≤ eta_i·eta_v
+0.5203 : 4·eta_i + T·eta_i²/(0.5·rho·V²·A_prop) ≤ 4

UAV.Mission.Return.AircraftPerf.WingAero
+0.1323  : 2.56·C_L^5.881/(Re^1.541·tau^3.319·C_Dp^2.617) + 3.82e-09·tau^6.229/(C_L^0.914·Re^1.379·C_Dp^9.57) + 0.00215·Re^0.1441·tau^0.03325/(C_L^0.0079·C_Dp^0.7337) + 1.19e+04·C_L^9.783·tau^1.764/(Re^0.998·C_Dp^0.909) + 6.14e-06·C_L^6.535/(Re^0.995·tau^0.521·C_Dp^5.192) ≤ 1
+0.01266 : Re = rho/mu·V·(S/A)^0.5

UAV.Mission.SprintCondition
+0.3708 : V ≥ V_reqt
+0.1254 : P_max ≥ T·V/eta_0

UAV.Mission.SprintCondition.AircraftPerf
+0.1329 : C_D ≥ CDA0/S + C_Dp + C_Di
+0.1329 : T ≥ 0.5·rho·C_D·S·V²

UAV.Mission.SprintCondition.AircraftPerf.PropulsionPerf
+0.1254 : eta_0 ≤ eta_eng·eta_prop
+0.1254 : eta_prop ≤ eta_i·eta_v
+0.1178 : 4·eta_i + T·eta_i²/(0.5·rho·V²·A_prop) ≤ 4

UAV.Mission.SprintCondition.AircraftPerf.WingAero
+0.06428 : 2.56·C_L^5.881/(Re^1.541·tau^3.319·C_Dp^2.617) + 3.82e-09·tau^6.229/(C_L^0.914·Re^1.379·C_Dp^9.57) + 0.00215·Re^0.1441·tau^0.03325/(C_L^0.0079·C_Dp^0.7337) + 1.19e+04·C_L^9.783·tau^1.764/(Re^0.998·C_Dp^0.909) + 6.14e-06·C_L^6.535/(Re^0.995·tau^0.521·C_Dp^5.192) ≤ 1

Condition Comparison
--------------------

Variable  Units  Outbound  Return    Sprint    Label
C_D              0.0129    0.0129    0.00788   total drag coefficient
C_Di             0.00565   0.00565   0.000256  induced drag coefficient
C_Dp             0.00555   0.00556   0.0059    profile drag coefficient
C_L              0.552     0.552     0.118     wing lift coefficient
Re               4.72e+06  4.48e+06  1.02e+07  Reynolds number
T         [N]    816       738       2.34e+03  thrust force
V         [m/s]  69.2      65.8      150       flight speed
W         [N]    3.49e+04  3.15e+04  3.49e+04  aircraft weight
W_fuel    [N]    3.73e+03  3.37e+03  —         fuel weight for this leg
eta_0            0.269     0.269     0.279     overall propulsive efficiency
eta_i            0.903     0.903     0.936     ideal propulsive efficiency
eta_prop         0.767     0.767     0.796     propeller efficiency
z_bre            0.102     0.102     —         Breguet range parameter
