Sample mission analysis for the Gulfstream 550 using an intermediate cruise Mach of 0.85. The range with 8 pax is just under 6000 nm. In this example the aircraft has been allowed to fly a continuous drift-up profile with no ATC restrictions on Flight Levels.
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 Loading manoeuvre sequence "sample-g550m85drift"...
 Sequence created with "Gulfstream G550" (15:52,Wed.Feb.15.2006)...done
 Summary of segments in the sequence:
 -----------------------------------------------
 Seg.  Speed mode   Thrust mode   Stop condition

   1.  v3           at-%mto       to alt 1500.
   2.  specify-cas  at-%mcl       to alt 10000.
   3.  specify-cas  at-%mcl       to mach 0.85
   4.  same-mach    at-%mcr       to dist +100.
   5.  same-mach    at-%mcr       to dist +200.
   6.  same-mach    at-%mcr       to dist +500.
   7.  same-mach    at-%mcr       to dist +2000.
   8.  same-mach    at-%mcr       to dist +2000.
   9.  same-mach    at-%mcr       to mass 53179.
  10.  same-mach    at-idle       to cas 300.
  11.  same-cas     at-idle       to alt 10000.
  12.  specify-cas  at-idle       to alt 1500.
  13.  vapp         match-grad    to alt 50.
 -----------------------------------------------
? 

 -----------------------------------------------------------------------------
 Manoeuvre segment 1 starts at:
 
 Initial Mass          90739.  lb.  (CL 0.93 trapezoidal)
 Initial Altitude         35.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          159.  kts  (V3)
 Flaps                    15   deg. 
 Undercarriage            up
 All eng.operative
 Thrust per engine     12381.  lbf. (100% MTO) 

 Climb/Descent rate     3128.  feet/min 
 Flightpath angle       11.0   deg. (grad.19.43%)
 True airspeed           159.  kts

 Fuel Flow rate        12520.  lb/hr 
 NOx emission rate     270.4   lb/hr
 HC  emission rate     0.251   lb/hr
 CO  emission rate      14.0   lb/hr 

 L/D ratio             13.83
 Total aircraft drag    6560.  lbf. 

 Segment 1 ends at total time = 0.5 mins, endmass = 90642.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +1465.   +28.4    +0.00      +97.3    +2.09   +0.002   +0.11
 Final :    1500.    28.4     0.00       97.3     2.09    0.002    0.11
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
              35.     0.0    0.000        0.0    12381.   159.   0.240   3128.  6560.   159.
             198.     3.1    0.000       10.9    12338.   159.   0.241   3121.  6560.   159.
             361.     6.3    0.000       21.7    12296.   159.   0.242   3113.  6559.   160.
             523.     9.4    0.000       32.5    12253.   159.   0.242   3106.  6558.   160.
             686.    12.5    0.000       43.3    12211.   159.   0.243   3098.  6557.   160.
             849.    15.7    0.000       54.2    12168.   159.   0.244   3090.  6556.   161.
            1012.    18.9    0.000       65.0    12126.   159.   0.244   3083.  6555.   161.
            1174.    22.0    0.000       75.7    12084.   159.   0.245   3075.  6555.   162.
            1337.    25.2    0.000       86.5    12041.   159.   0.246   3067.  6554.   162.
            1500.    28.4    0.000       97.3    11999.   159.   0.247   3059.  6553.   162.
 -----------------------------------------------------------------------------

 Acceleration to 250.kts in level flight at 1500.feet =0.20g:
 Time +24.6 sec, Dist +1.44 n.miles, Fuelburn +83.9 lb.
 NOx  +1.83 lb., HC +0.002 lb., CO +0.096 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 2 starts at:
 
 Initial Mass          90558.  lb.  (CL 0.38 trapezoidal)
 Initial Altitude       1500.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          250.  kts  (input)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      9172.  lbf. (100% MCL) 

 Climb/Descent rate     3525.  feet/min 
 Flightpath angle        7.8   deg. (grad.13.63%)
 True airspeed           255.  kts

 Fuel Flow rate        10565.  lb/hr 
 NOx emission rate     193.5   lb/hr
 HC  emission rate     0.216   lb/hr
 CO  emission rate      11.1   lb/hr 

 L/D ratio             18.14
 Total aircraft drag    4991.  lbf. 

 Segment 2 ends at total time = 3.5 mins, endmass = 90139.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +8500.   +155.   +11.68     +419.2    +7.42   +0.009   +0.46
 Final :   10000.    208.    13.12      600.4    11.34    0.013    0.66
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
            1500.    53.0    1.436      181.2    9172.    250.   0.388   3525.  4991.   255.
            1947.    60.7    1.980      203.5    9091.    250.   0.391   3502.  4991.   257.
            2395.    68.4    2.531      225.8    9012.    250.   0.394   3478.  4990.   259.
            2842.    76.1    3.089      248.1    8933.    250.   0.397   3455.  4990.   260.
            3289.    83.9    3.654      270.3    8855.    250.   0.400   3432.  4989.   262.
            3737.    91.7    4.226      292.5    8784.    250.   0.404   3412.  4989.   264.
            4184.    99.6    4.806      314.6    8713.    250.   0.407   3392.  4988.   265.
            4632.   107.6    5.393      336.7    8642.    250.   0.410   3372.  4987.   267.
            5079.   115.6    5.987      358.8    8570.    250.   0.413   3351.  4987.   269.
            5526.   123.6    6.589      380.9    8491.    250.   0.417   3325.  4986.   270.
            5974.   131.7    7.200      402.9    8412.    250.   0.420   3299.  4985.   272.
            6421.   139.9    7.819      424.9    8333.    250.   0.424   3273.  4985.   274.
            6868.   148.1    8.448      446.9    8255.    250.   0.427   3247.  4984.   276.
            7316.   156.4    9.086      468.8    8178.    250.   0.431   3221.  4983.   278.
            7763.   164.8    9.733      490.8    8100.    250.   0.434   3194.  4982.   279.
            8211.   173.2    10.39      512.7    8023.    250.   0.438   3168.  4981.   281.
            8658.   181.7    11.06      534.7    7947.    250.   0.441   3141.  4981.   283.
            9105.   190.3    11.73      556.6    7871.    250.   0.445   3114.  4980.   285.
            9553.   199.0    12.42      578.5    7795.    250.   0.449   3087.  4979.   287.
           10000.   207.7    13.12      600.4    7720.    250.   0.452   3060.  4978.   289.
 -----------------------------------------------------------------------------

 Acceleration to 300.kts in level flight at 10000.feet =0.13g:
 Time +23.2 sec, Dist +2.05 n.miles, Fuelburn +65.7 lb.
 NOx  +1.32 lb., HC +0.002 lb., CO +0.082 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 3 starts at:
 
 Initial Mass          90073.  lb.  (CL 0.27 trapezoidal)
 Initial Altitude      10000.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (input)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      7290.  lbf. (100% MCL) 

 Climb/Descent rate     2941.  feet/min 
 Flightpath angle        4.8   deg. (grad.8.41%)
 True airspeed           345.  kts

 Fuel Flow rate         9107.  lb/hr 
 NOx emission rate     160.1   lb/hr
 HC  emission rate     0.211   lb/hr
 CO  emission rate      10.6   lb/hr 

 L/D ratio             15.38
 Total aircraft drag    5855.  lbf. 

 Segment 3 ends at total time = 17.0 mins, endmass = 88582.lb.(1.95g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:  +23639.   +789.   +93.82    +1491.0   +21.95   +0.043   +2.10
 Final :   33639.   1020.   108.98     2157.1    34.61    0.058    2.84
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           10000.   230.9    15.17      666.1    7290.    300.   0.541   2941.  5855.   345.
           11244.   256.7    17.67      730.5    7086.    300.   0.553   2844.  5846.   352.
           12488.   283.4    20.30      795.5    6885.    300.   0.566   2745.  5835.   358.
           13732.   311.1    23.08      861.0    6687.    300.   0.579   2646.  5824.   365.
           14977.   339.9    26.02      927.2    6492.    300.   0.593   2546.  5812.   371.
           16221.   369.8    29.14      994.2    6301.    300.   0.607   2446.  5799.   378.
           17465.   400.9    32.44     1062.2    6122.    300.   0.621   2351.  5785.   385.
           18709.   433.4    35.94     1131.2    5946.    300.   0.636   2256.  5770.   392.
           19953.   467.2    39.67     1201.4    5772.    300.   0.651   2160.  5754.   400.
           21197.   502.6    43.63     1273.0    5601.    300.   0.666   2063.  5737.   407.
           22441.   539.6    47.87     1346.0    5433.    300.   0.682   1967.  5720.   415.
           23686.   578.6    52.40     1420.7    5269.    300.   0.699   1870.  5700.   423.
           24930.   619.6    57.27     1497.2    5108.    300.   0.716   1773.  5683.   431.
           26174.   662.9    62.51     1575.9    4947.    300.   0.733   1673.  5665.   439.
           27418.   709.0    68.18     1657.1    4791.    300.   0.751   1573.  5649.   448.
           28662.   758.1    74.35     1741.4    4639.    300.   0.770   1470.  5643.   456.
           29906.   810.9    81.12     1829.6    4493.    300.   0.789   1359.  5662.   465.
           31151.   868.9    88.69     1923.7    4345.    300.   0.809   1222.  5733.   474.
           32395.   935.6    97.56     2028.6    4203.    300.   0.829   1035.  5927.   484.
           33639.   1020.   108.98     2157.1    4065.    300.   0.850   777.   6290.   493.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 4 starts at:
 
 Initial Mass          88582.  lb.  (CL 0.29 trapezoidal)
 Initial Altitude      33639.  feet (1.95g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3683.  lbf. (100% MCR) 

 Climb/Descent rate      672.  feet/min 
 Flightpath angle        0.8   deg. (grad.1.35%)
 True airspeed           493.  kts

 Fuel Flow rate         4915.  lb/hr 
 NOx emission rate      56.4   lb/hr
 HC  emission rate     0.215   lb/hr
 CO  emission rate      13.8   lb/hr 

 L/D ratio             14.09
 Total aircraft drag    6288.  lbf. 

 Segment 4 ends at total time = 29.3 mins, endmass = 87690.lb.(1.52g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +5300.   +737.  +100.00     +892.2    +9.48   +0.046   +3.09
 Final :   38939.   1757.   208.98     3049.3    44.09    0.103    5.93
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           33639.   1020.   108.98     2157.1    3683.    300.   0.850   672.   6288.   493.
           34069.   1058.   114.25     2209.3    3648.    297.   0.850   669.   6223.   492.
           34497.   1097.   119.51     2261.0    3613.    294.   0.850   664.   6159.   491.
           34922.   1135.   124.77     2312.2    3579.    291.   0.850   658.   6098.   490.
           35336.   1174.   130.04     2362.7    3524.    289.   0.850   626.   6039.   489.
           35729.   1213.   135.30     2412.4    3468.    286.   0.850   589.   5986.   488.
           36081.   1252.   140.56     2461.3    3415.    284.   0.850   500.   5937.   488.
           36395.   1290.   145.83     2509.6    3370.    282.   0.850   471.   5899.   488.
           36691.   1329.   151.09     2557.2    3328.    280.   0.850   443.   5864.   488.
           36969.   1368.   156.35     2604.2    3288.    278.   0.850   416.   5832.   488.
           37231.   1407.   161.62     2650.7    3250.    276.   0.850   391.   5804.   488.
           37476.   1446.   166.88     2696.6    3215.    275.   0.850   366.   5777.   488.
           37705.   1485.   172.14     2742.1    3182.    273.   0.850   343.   5754.   488.
           37920.   1524.   177.41     2787.1    3151.    272.   0.850   320.   5732.   488.
           38121.   1562.   182.67     2831.7    3122.    271.   0.850   299.   5712.   488.
           38308.   1601.   187.93     2875.9    3095.    270.   0.850   279.   5694.   488.
           38483.   1640.   193.20     2919.7    3070.    269.   0.850   260.   5678.   488.
           38646.   1679.   198.46     2963.2    3047.    268.   0.850   243.   5663.   488.
           38797.   1718.   203.72     3006.4    3025.    267.   0.850   226.   5649.   488.
           38939.   1757.   208.98     3049.3    3005.    266.   0.850   210.   5636.   488.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 5 starts at:
 
 Initial Mass          87690.  lb.  (CL 0.37 trapezoidal)
 Initial Altitude      38939.  feet (1.53g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          266.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3025.  lbf. (100% MCR) 

 Climb/Descent rate      227.  feet/min 
 Flightpath angle        0.3   deg. (grad.0.46%)
 True airspeed           488.  kts

 Fuel Flow rate         3984.  lb/hr 
 NOx emission rate      40.3   lb/hr
 HC  emission rate     0.224   lb/hr
 CO  emission rate      15.2   lb/hr 

 L/D ratio             15.53
 Total aircraft drag    5647.  lbf. 

 Segment 5 ends at total time = 53.9 mins, endmass = 86160.lb.(1.41g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +1952.  +1477.  +200.00    +1530.0   +14.98   +0.092   +6.22
 Final :   40891.   3234.   408.98     4579.3    59.07    0.195   12.15
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           38939.   1757.   208.98     3049.3    3025.    266.   0.850   227.   5647.   488.
           39212.   1835.   219.51     3134.7    2984.    264.   0.850   195.   5622.   488.
           39447.   1912.   230.04     3219.0    2949.    263.   0.850   167.   5602.   488.
           39648.   1990.   240.56     3302.5    2919.    261.   0.850   143.   5584.   488.
           39821.   2068.   251.09     3385.1    2893.    260.   0.850   123.   5569.   488.
           39969.   2145.   261.62     3467.1    2872.    259.   0.850   106.   5556.   488.
           40098.   2223.   272.14     3548.5    2854.    259.   0.850   93.    5545.   488.
           40210.   2301.   282.67     3629.4    2839.    258.   0.850   81.    5534.   488.
           40310.   2379.   293.20     3709.9    2826.    257.   0.850   72.    5525.   488.
           40397.   2456.   303.72     3790.1    2814.    257.   0.850   63.    5517.   488.
           40474.   2534.   314.25     3870.0    2804.    256.   0.850   56.    5509.   488.
           40542.   2612.   324.77     3949.6    2794.    256.   0.850   49.    5502.   488.
           40603.   2690.   335.30     4028.9    2786.    256.   0.850   44.    5495.   488.
           40657.   2767.   345.83     4108.0    2779.    255.   0.850   40.    5489.   488.
           40705.   2845.   356.35     4187.0    2773.    255.   0.850   36.    5483.   488.
           40749.   2923.   366.88     4265.7    2767.    255.   0.850   32.    5477.   488.
           40789.   3000.   377.41     4344.3    2761.    255.   0.850   29.    5471.   488.
           40826.   3078.   387.93     4422.7    2757.    254.   0.850   27.    5466.   488.
           40860.   3156.   398.46     4501.1    2752.    254.   0.850   25.    5460.   488.
           40891.   3234.   408.98     4579.3    2748.    254.   0.850   23.    5455.   488.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 6 starts at:
 
 Initial Mass          86160.  lb.  (CL 0.40 trapezoidal)
 Initial Altitude      40891.  feet (1.42g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          254.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2765.  lbf. (100% MCR) 

 Climb/Descent rate       39.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.08%)
 True airspeed           488.  kts

 Fuel Flow rate         3641.  lb/hr 
 NOx emission rate      35.2   lb/hr
 HC  emission rate     0.224   lb/hr
 CO  emission rate      15.1   lb/hr 

 L/D ratio             15.78
 Total aircraft drag    5462.  lbf. 

 Segment 6 ends at total time = 115.4 mins, endmass = 82529.lb.(1.41g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:    +998.  +3692.  +500.00    +3630.5   +34.62   +0.229  +15.50
 Final :   41889.   6926.   908.98     8209.8    93.68    0.424   27.65
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           40891.   3234.   408.98     4579.3    2765.    254.   0.850   39.    5462.   488.
           41001.   3428.   435.30     4775.2    2749.    253.   0.850   29.    5447.   488.
           41086.   3622.   461.62     4970.2    2737.    253.   0.850   23.    5433.   488.
           41155.   3817.   487.93     5164.4    2727.    252.   0.850   19.    5421.   488.
           41215.   4011.   514.25     5358.0    2719.    252.   0.850   17.    5409.   488.
           41268.   4205.   540.56     5551.0    2712.    252.   0.850   16.    5397.   488.
           41318.   4399.   566.88     5743.6    2706.    252.   0.850   15.    5386.   488.
           41365.   4594.   593.20     5935.7    2700.    251.   0.850   14.    5375.   488.
           41411.   4788.   619.51     6127.4    2694.    251.   0.850   14.    5363.   488.
           41456.   4982.   645.83     6318.7    2688.    251.   0.850   14.    5352.   488.
           41500.   5177.   672.14     6509.6    2682.    250.   0.850   14.    5341.   488.
           41544.   5371.   698.46     6700.0    2677.    250.   0.850   14.    5330.   488.
           41588.   5565.   724.77     6890.1    2671.    250.   0.850   13.    5320.   488.
           41631.   5760.   751.09     7079.8    2666.    250.   0.850   13.    5309.   488.
           41674.   5954.   777.41     7269.1    2660.    249.   0.850   13.    5298.   488.
           41718.   6148.   803.72     7458.0    2655.    249.   0.850   13.    5287.   488.
           41761.   6343.   830.04     7646.5    2649.    249.   0.850   13.    5276.   488.
           41804.   6537.   856.35     7834.7    2644.    249.   0.850   13.    5265.   488.
           41846.   6731.   882.67     8022.4    2638.    248.   0.850   13.    5255.   488.
           41889.   6926.   908.98     8209.8    2633.    248.   0.850   13.    5244.   488.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 7 starts at:
 
 Initial Mass          82529.  lb.  (CL 0.40 trapezoidal)
 Initial Altitude      41889.  feet (1.41g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          248.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2638.  lbf. (100% MCR) 

 Climb/Descent rate       18.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.04%)
 True airspeed           488.  kts

 Fuel Flow rate         3475.  lb/hr 
 NOx emission rate      32.8   lb/hr
 HC  emission rate     0.224   lb/hr
 CO  emission rate      15.1   lb/hr 

 L/D ratio             15.73
 Total aircraft drag    5246.  lbf. 

 Segment 7 ends at total time = 361.6 mins, endmass = 69353.lb.(1.45g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +2964. +14768. +2000.00   +13176.7  +119.51   +0.921  +62.55
 Final :   44853.  21693.  2908.98    21386.5   213.20    1.346   90.20
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           41889.   6926.   908.98     8209.8    2638.    248.   0.850   18.    5246.   488.
           42071.   7703.  1014.25     8955.7    2608.    247.   0.850   10.    5200.   488.
           42231.   8480.  1119.51     9695.0    2592.    246.   0.850   15.    5160.   488.
           42402.   9257.  1224.77    10428.6    2568.    245.   0.850   11.    5117.   488.
           42564.  10034.  1330.04    11156.0    2549.    244.   0.850   14.    5076.   488.
           42729.  10812.  1435.30    11877.6    2527.    243.   0.850   12.    5034.   488.
           42890.  11589.  1540.56    12593.2    2507.    242.   0.850   13.    4994.   488.
           43051.  12366.  1645.83    13303.1    2486.    242.   0.850   12.    4953.   488.
           43209.  13143.  1751.09    14007.1    2466.    241.   0.850   12.    4913.   488.
           43366.  13921.  1856.35    14705.4    2446.    240.   0.850   12.    4873.   488.
           43521.  14698.  1961.62    15398.1    2426.    239.   0.850   12.    4834.   488.
           43675.  15475.  2066.88    16085.2    2407.    238.   0.850   12.    4795.   488.
           43828.  16252.  2172.14    16766.7    2387.    237.   0.850   12.    4757.   488.
           43979.  17030.  2277.41    17442.7    2368.    236.   0.850   12.    4719.   488.
           44128.  17807.  2382.67    18113.3    2349.    236.   0.850   12.    4681.   488.
           44276.  18584.  2487.93    18778.5    2330.    235.   0.850   11.    4644.   488.
           44422.  19361.  2593.20    19438.4    2311.    234.   0.850   11.    4607.   488.
           44567.  20139.  2698.46    20092.9    2293.    233.   0.850   11.    4570.   488.
           44711.  20916.  2803.72    20742.3    2275.    232.   0.850   11.    4534.   488.
           44853.  21693.  2908.98    21386.5    2257.    232.   0.850   11.    4498.   488.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 8 starts at:
 
 Initial Mass          69353.  lb.  (CL 0.39 trapezoidal)
 Initial Altitude      44853.  feet (1.45g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          232.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2263.  lbf. (100% MCR) 

 Climb/Descent rate       16.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.03%)
 True airspeed           488.  kts

 Fuel Flow rate         2980.  lb/hr 
 NOx emission rate      25.9   lb/hr
 HC  emission rate     0.226   lb/hr
 CO  emission rate      15.5   lb/hr 

 L/D ratio             15.40
 Total aircraft drag    4503.  lbf. 

 Segment 8 ends at total time = 607.7 mins, endmass = 58058.lb.(1.48g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +3248. +14768. +2000.00   +11294.8   +94.49   +0.927  +63.48
 Final :   48100.  36461.  4908.98    32681.3   307.69    2.272  153.68
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           44853.  21693.  2908.98    21386.5    2263.    232.   0.850   16.    4503.   488.
           45012.  22470.  3014.25    22026.3    2238.    231.   0.850   9.     4464.   488.
           45177.  23248.  3119.51    22661.0    2227.    230.   0.850   17.    4430.   488.
           45373.  24025.  3224.77    23291.0    2205.    229.   0.850   13.    4392.   488.
           45553.  24802.  3330.04    23915.4    2188.    228.   0.850   15.    4355.   488.
           45738.  25579.  3435.30    24534.7    2169.    227.   0.850   14.    4319.   488.
           45918.  26357.  3540.56    25148.7    2151.    226.   0.850   14.    4283.   488.
           46097.  27134.  3645.83    25757.6    2132.    225.   0.850   14.    4247.   488.
           46273.  27911.  3751.09    26361.4    2115.    224.   0.850   14.    4212.   488.
           46449.  28688.  3856.35    26960.1    2097.    223.   0.850   13.    4177.   488.
           46622.  29466.  3961.62    27553.8    2080.    222.   0.850   13.    4142.   488.
           46793.  30243.  4066.88    28142.6    2062.    221.   0.850   13.    4108.   488.
           46963.  31020.  4172.14    28726.5    2045.    221.   0.850   13.    4074.   488.
           47130.  31797.  4277.41    29305.6    2028.    220.   0.850   13.    4040.   488.
           47296.  32574.  4382.67    29879.9    2012.    219.   0.850   13.    4007.   488.
           47461.  33352.  4487.93    30449.5    1995.    218.   0.850   13.    3974.   488.
           47623.  34129.  4593.20    31014.3    1979.    217.   0.850   12.    3942.   488.
           47784.  34906.  4698.46    31574.6    1962.    216.   0.850   12.    3910.   488.
           47943.  35683.  4803.72    32130.2    1946.    216.   0.850   12.    3878.   488.
           48100.  36461.  4908.98    32681.3    1930.    215.   0.850   12.    3847.   488.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 9 starts at:
 
 Initial Mass          58058.  lb.  (CL 0.38 trapezoidal)
 Initial Altitude      48100.  feet (1.48g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          215.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      1933.  lbf. (100% MCR) 

 Climb/Descent rate       13.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.03%)
 True airspeed           488.  kts

 Fuel Flow rate         2545.  lb/hr 
 NOx emission rate      20.4   lb/hr
 HC  emission rate     0.226   lb/hr
 CO  emission rate      15.5   lb/hr 

 L/D ratio             15.08
 Total aircraft drag    3850.  lbf. 

 Segment 9 ends at total time = 727.1 mins, endmass = 53179.lb.(1.52g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +1382.  +7164.  +970.25    +4878.7   +38.38   +0.452  +31.15
 Final :   49483.  43625.  5879.24    37559.9   346.06    2.724  184.83
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           48100.  36461.  4908.98    32681.3    1933.    215.   0.850   13.    3850.   488.
           48179.  36825.  4958.27    32938.1    1925.    214.   0.850   12.    3835.   488.
           48253.  37190.  5007.76    33194.8    1917.    214.   0.850   12.    3820.   488.
           48327.  37557.  5057.44    33451.6    1910.    214.   0.850   12.    3806.   488.
           48400.  37925.  5107.32    33708.4    1903.    213.   0.850   12.    3791.   488.
           48472.  38295.  5157.38    33965.1    1895.    213.   0.850   12.    3777.   488.
           48545.  38666.  5207.64    34221.9    1888.    213.   0.850   12.    3762.   488.
           48618.  39038.  5258.10    34478.7    1881.    212.   0.850   12.    3748.   488.
           48691.  39412.  5308.75    34735.5    1873.    212.   0.850   12.    3733.   488.
           48763.  39788.  5359.60    34992.2    1866.    211.   0.850   12.    3719.   488.
           48836.  40165.  5410.64    35249.0    1859.    211.   0.850   12.    3705.   488.
           48908.  40543.  5461.89    35505.8    1851.    211.   0.850   11.    3690.   488.
           48980.  40923.  5513.34    35762.5    1844.    210.   0.850   11.    3676.   488.
           49052.  41304.  5564.99    36019.3    1837.    210.   0.850   11.    3661.   488.
           49124.  41687.  5616.85    36276.1    1830.    210.   0.850   11.    3647.   488.
           49196.  42072.  5668.91    36532.9    1823.    209.   0.850   11.    3633.   488.
           49268.  42458.  5721.18    36789.6    1815.    209.   0.850   11.    3618.   488.
           49340.  42845.  5773.66    37046.4    1808.    209.   0.850   11.    3604.   488.
           49411.  43234.  5826.34    37303.2    1801.    208.   0.850   11.    3590.   488.
           49483.  43625.  5879.24    37559.9    1794.    208.   0.850   11.    3576.   488.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 10 starts at:
 
 Initial Mass          53179.  lb.  (CL 0.37 trapezoidal)
 Initial Altitude      49483.  feet (1.52g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          208.  kts  (fixed Mach 0.850)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine       444.  lbf. (idle) 

 Climb/Descent rate    -2496.  feet/min 
 Flightpath angle       -2.9   deg. (grad.-5.05%)
 True airspeed           488.  kts

 Fuel Flow rate          904.  lb/hr 
 NOx emission rate       3.9   lb/hr
 HC  emission rate     0.789   lb/hr
 CO  emission rate      29.0   lb/hr 

 L/D ratio             14.87
 Total aircraft drag    3576.  lbf. 

 Segment 10 ends at total time = 731.8 mins, endmass = 53109.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:  -15842.   +286.   +38.73      +70.1    +0.29   +0.113   +3.16
 Final :   33641.  43911.  5917.97    37630.0   346.36    2.837  187.99
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           49483.  43625.  5879.24    37559.9    444.     208.   0.850   -2496. 3576.   488.
           48649.  43645.  5881.93    37564.9    444.     212.   0.850   -2538. 3621.   488.
           47815.  43664.  5884.58    37569.8    444.     216.   0.850   -2586. 3673.   488.
           46981.  43683.  5887.17    37574.7    444.     220.   0.850   -2640. 3731.   488.
           46148.  43702.  5889.71    37579.4    444.     225.   0.850   -2700. 3795.   488.
           45314.  43720.  5892.19    37584.0    444.     229.   0.850   -2765. 3865.   488.
           44480.  43738.  5894.60    37588.4    431.     234.   0.850   -2860. 3941.   488.
           43646.  43755.  5896.92    37592.7    411.     238.   0.850   -2974. 4022.   488.
           42812.  43772.  5899.15    37596.8    390.     243.   0.850   -3093. 4109.   488.
           41979.  43788.  5901.30    37600.7    369.     248.   0.850   -3217. 4201.   488.
           41145.  43803.  5903.37    37604.5    349.     253.   0.850   -3347. 4299.   488.
           40311.  43818.  5905.35    37608.0    328.     257.   0.850   -3482. 4403.   488.
           39477.  43832.  5907.26    37611.5    294.     262.   0.850   -3647. 4512.   488.
           38643.  43845.  5909.07    37614.7    253.     268.   0.850   -3831. 4628.   488.
           37810.  43858.  5910.80    37617.7    211.     273.   0.850   -4021. 4749.   488.
           36976.  43870.  5912.44    37620.6    170.     278.   0.850   -4217. 4877.   488.
           36142.  43881.  5914.01    37623.3    129.     283.   0.850   -4418. 5010.   488.
           35308.  43892.  5915.44    37625.8    87.      289.   0.850   -5142. 5155.   489.
           34474.  43901.  5916.73    37627.9    46.      294.   0.850   -5404. 5306.   491.
           33641.  43911.  5917.97    37630.0    4.       300.   0.850   -5673. 5463.   493.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 11 starts at:
 
 Initial Mass          53109.  lb.  (CL 0.17 trapezoidal)
 Initial Altitude      33641.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (fixed)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine         4.  lbf. (idle) 

 Climb/Descent rate    -3841.  feet/min 
 Flightpath angle       -4.4   deg. (grad.-7.69%)
 True airspeed           493.  kts

 Fuel Flow rate          815.  lb/hr 
 NOx emission rate       3.2   lb/hr
 HC  emission rate     1.551   lb/hr
 CO  emission rate      39.5   lb/hr 

 L/D ratio              9.72
 Total aircraft drag    5463.  lbf. 

 Segment 11 ends at total time = 738.5 mins, endmass = 53026.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:  -23641.   +400.   +46.01      +82.5    +0.32   +0.148   +3.72
 Final :   10000.  44311.  5963.98    37712.5   346.67    2.985  191.71
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           33641.  43911.  5917.97    37630.0    4.       300.   0.850   -3841. 5463.   493.
           32396.  43931.  5920.68    37634.5    -30.     300.   0.829   -3626. 5136.   484.
           31152.  43951.  5923.46    37639.1    -62.     300.   0.809   -3528. 4980.   474.
           29908.  43973.  5926.23    37643.8    -97.     300.   0.789   -3499. 4917.   465.
           28664.  43994.  5928.97    37648.4    -113.    300.   0.770   -3476. 4901.   456.
           27419.  44016.  5931.67    37653.2    -136.    300.   0.751   -3477. 4909.   448.
           26175.  44037.  5934.31    37657.9    -165.    300.   0.733   -3493. 4926.   439.
           24931.  44058.  5936.88    37662.4    -201.    300.   0.716   -3517. 4947.   431.
           23687.  44079.  5939.39    37666.8    -241.    300.   0.699   -3545. 4966.   423.
           22442.  44100.  5941.84    37671.1    -266.    300.   0.682   -3552. 4987.   415.
           21198.  44121.  5944.24    37675.3    -290.    300.   0.666   -3556. 5007.   407.
           19954.  44142.  5946.59    37679.4    -312.    300.   0.651   -3557. 5025.   400.
           18710.  44163.  5948.90    37683.5    -335.    300.   0.636   -3555. 5042.   392.
           17465.  44184.  5951.17    37687.7    -362.    300.   0.621   -3558. 5058.   385.
           16221.  44205.  5953.39    37691.8    -395.    300.   0.607   -3566. 5073.   378.
           14977.  44226.  5955.57    37695.8    -423.    300.   0.593   -3566. 5087.   371.
           13733.  44247.  5957.71    37699.9    -443.    300.   0.579   -3554. 5100.   365.
           12488.  44268.  5959.83    37704.0    -459.    300.   0.566   -3537. 5112.   358.
           11244.  44289.  5961.91    37708.2    -471.    300.   0.553   -3516. 5123.   352.
           10000.  44311.  5963.98    37712.5    -481.    300.   0.541   -3490. 5133.   345.
 -----------------------------------------------------------------------------

 Deceleration to 250.kts in level flight at 10000.feet =-0.10g:
 Time +29.9 sec, Dist +2.62 n.miles, Fuelburn +6.3 lb.
 NOx  +0.02 lb., HC +0.010 lb., CO +0.248 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 12 starts at:
 
 Initial Mass          53020.  lb.  (CL 0.22 trapezoidal)
 Initial Altitude      10000.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          250.  kts  (input)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      -298.  lbf. (idle) 

 Climb/Descent rate    -2274.  feet/min 
 Flightpath angle       -4.4   deg. (grad.-7.78%)
 True airspeed           289.  kts

 Fuel Flow rate          774.  lb/hr 
 NOx emission rate       3.0   lb/hr
 HC  emission rate     1.220   lb/hr
 CO  emission rate      30.3   lb/hr 

 L/D ratio             13.33
 Total aircraft drag    3979.  lbf. 

 Segment 12 ends at total time = 742.9 mins, endmass = 52961.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   -8500.   +236.   +17.79      +59.5    +0.24   +0.084   +2.10
 Final :    1500.  44577.  5984.39    37778.3   346.94    3.080  194.06
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           10000.  44341.  5966.60    37718.8    -298.    250.   0.452   -2274. 3979.   289.
            9553.  44353.  5967.54    37721.4    -298.    250.   0.449   -2264. 3980.   287.
            9105.  44364.  5968.49    37724.0    -299.    250.   0.445   -2253. 3980.   285.
            8658.  44376.  5969.43    37726.7    -298.    250.   0.441   -2242. 3981.   283.
            8211.  44388.  5970.37    37729.4    -298.    250.   0.438   -2231. 3982.   281.
            7763.  44400.  5971.31    37732.2    -297.    250.   0.434   -2219. 3983.   279.
            7316.  44413.  5972.25    37735.1    -296.    250.   0.431   -2207. 3984.   278.
            6868.  44425.  5973.19    37738.0    -295.    250.   0.427   -2195. 3984.   276.
            6421.  44437.  5974.12    37741.0    -294.    250.   0.424   -2183. 3985.   274.
            5974.  44449.  5975.06    37744.0    -292.    250.   0.420   -2171. 3985.   272.
            5526.  44462.  5975.99    37747.1    -290.    250.   0.417   -2158. 3986.   270.
            5079.  44474.  5976.93    37750.3    -288.    250.   0.413   -2146. 3987.   269.
            4632.  44487.  5977.86    37753.5    -286.    250.   0.410   -2133. 3987.   267.
            4184.  44499.  5978.79    37756.9    -283.    250.   0.407   -2120. 3987.   265.
            3737.  44512.  5979.73    37760.3    -281.    250.   0.404   -2107. 3988.   264.
            3289.  44525.  5980.66    37763.7    -278.    250.   0.400   -2093. 3988.   262.
            2842.  44538.  5981.59    37767.3    -275.    250.   0.397   -2081. 3988.   260.
            2395.  44551.  5982.52    37770.9    -273.    250.   0.394   -2068. 3989.   259.
            1947.  44564.  5983.46    37774.6    -271.    250.   0.391   -2056. 3989.   257.
            1500.  44577.  5984.39    37778.3    -269.    250.   0.388   -2043. 3989.   255.
 -----------------------------------------------------------------------------

 Deceleration to 111.kts in level flight at 1500.feet =-0.23g:
 Time +31.8 sec, Dist +1.47 n.miles, Fuelburn +9.8 lb.
 NOx  +0.04 lb., HC +0.012 lb., CO +0.310 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 13 starts at:
 
 Initial Mass          52951.  lb.  (CL 1.11 trapezoidal)
 Initial Altitude       1500.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          111.  kts  (Vapp)
 Flaps                    30   deg. 
 Undercarriage          down
 All eng.operative
 Thrust per engine      2112.  lbf. (match grad.) =18.9%MCL

 Climb/Descent rate     -603.  feet/min 
 Flightpath angle       -3.0   deg. (grad.-5.24%)
 True airspeed           114.  kts

 Fuel Flow rate         3326.  lb/hr 
 NOx emission rate      25.7   lb/hr
 HC  emission rate     0.170   lb/hr
 CO  emission rate      16.3   lb/hr 

 L/D ratio              7.52
 Total aircraft drag    7046.  lbf. 

 Segment 13 ends at total time = 745.9 mins, endmass = 52814.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   -1450.   +146.    +0.00     +136.9    +1.06   +0.007   +0.66
 Final :      50.  44755.  5985.86    37925.0   348.04    3.099  195.03
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
            1500.  44609.    0.000    37788.1    2112.    111.   0.173   -603.  7046.   114.
            1339.  44625.    0.000    37803.0    2112.    111.   0.172   -601.  7044.   113.
            1178.  44641.    0.000    37817.9    2111.    111.   0.172   -600.  7042.   113.
            1017.  44657.    0.000    37833.0    2111.    111.   0.171   -598.  7040.   113.
             856.  44673.    0.000    37848.1    2111.    111.   0.171   -597.  7038.   112.
             694.  44689.    0.000    37863.3    2110.    111.   0.170   -595.  7037.   112.
             533.  44705.    0.000    37878.6    2110.    111.   0.170   -594.  7035.   112.
             372.  44722.    0.000    37894.0    2109.    111.   0.169   -593.  7033.   112.
             211.  44738.    0.000    37909.4    2109.    111.   0.168   -591.  7031.   111.
              50.  44755.    0.000    37925.0    2108.    111.   0.168   -590.  7029.   111.
 -----------------------------------------------------------------------------
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