Sample mission analysis for the Gulfstream 550 using high-speed cruise mode at Mach 0.87. The range with 8 pax is just under 5000 nm. In this example, step-ups have been allowed at +2000 ft intervals (may cause ATC tachycardia).
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 Loading manoeuvre sequence "sample-g550m87step"...
 Sequence created with "Gulfstream G550" (12:44,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.  same-cas     at-%mcl       to mach 0.82
   4.  same-mach    at-%mcl       to alt 35000.
   5.  specify-mach level-cruise  to next stepup
   6.  same-mach    at-%mcl       to dalt 2000.
   7.  same-mach    level-cruise  to next stepup
   8.  same-mach    at-%mcl       to dalt 2000.
   9.  same-mach    level-cruise  to next stepup
  10.  same-mach    at-%mcl       to dalt 2000.
  11.  same-mach    level-cruise  to next stepup
  12.  same-mach    at-%mcl       to dalt 2000.
  13.  same-mach    level-cruise  to next stepup
  14.  same-mach    at-%mcl       to dalt 2000.
  15.  same-mach    level-cruise  to mass 53168.
  16.  specify-mach at-idle       to cas 300.
  17.  same-cas     at-idle       to alt 10000.
  18.  specify-cas  at-idle       to alt 1500.
  19.  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 300.kts in level flight at 1500.feet =0.19g:
 Time +40.4 sec, Dist +2.67 n.miles, Fuelburn +138.1 lb.
 NOx  +3.05 lb., HC +0.003 lb., CO +0.159 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 2 starts at:
 
 Initial Mass          90504.  lb.  (CL 0.26 trapezoidal)
 Initial Altitude       1500.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (input)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      8654.  lbf. (100% MCL) 

 Climb/Descent rate     3504.  feet/min 
 Flightpath angle        6.4   deg. (grad.11.30%)
 True airspeed           306.  kts

 Fuel Flow rate        10700.  lb/hr 
 NOx emission rate     202.5   lb/hr
 HC  emission rate     0.219   lb/hr
 CO  emission rate      11.4   lb/hr 

 L/D ratio             15.33
 Total aircraft drag    5905.  lbf. 

 Segment 2 ends at total time = 3.8 mins, endmass = 90070.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +8500.   +158.   +14.30     +433.5    +7.95   +0.009   +0.48
 Final :   10000.    227.    16.97      668.9    13.08    0.014    0.75
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
            1500.    68.8    2.674      235.4    8654.    300.   0.465   3504.  5905.   306.
            1947.    76.5    3.330      258.2    8583.    300.   0.469   3479.  5903.   308.
            2395.    84.3    3.995      280.9    8513.    300.   0.473   3453.  5901.   310.
            2842.    92.1    4.669      303.6    8443.    300.   0.476   3427.  5898.   312.
            3289.    99.9    5.353      326.3    8373.    300.   0.480   3401.  5896.   314.
            3737.   107.8    6.046      349.0    8304.    300.   0.484   3375.  5894.   316.
            4184.   115.8    6.749      371.7    8234.    300.   0.488   3348.  5892.   318.
            4632.   123.9    7.462      394.5    8165.    300.   0.492   3321.  5889.   320.
            5079.   132.0    8.186      417.2    8095.    300.   0.495   3294.  5887.   322.
            5526.   140.2    8.921      439.9    8020.    300.   0.499   3262.  5885.   324.
            5974.   148.5    9.667      462.7    7945.    300.   0.503   3230.  5882.   326.
            6421.   156.8    10.43      485.4    7870.    300.   0.507   3198.  5879.   328.
            6868.   165.2    11.20      508.3    7796.    300.   0.511   3166.  5877.   330.
            7316.   173.8    11.98      531.1    7722.    300.   0.516   3134.  5874.   332.
            7763.   182.4    12.78      554.0    7649.    300.   0.520   3102.  5871.   334.
            8211.   191.1    13.59      576.9    7576.    300.   0.524   3070.  5868.   337.
            8658.   199.9    14.41      599.8    7504.    300.   0.528   3038.  5865.   339.
            9105.   208.7    15.25      622.8    7432.    300.   0.532   3005.  5862.   341.
            9553.   217.7    16.11      645.8    7361.    300.   0.537   2973.  5858.   343.
           10000.   226.8    16.97      668.9    7290.    300.   0.541   2941.  5855.   345.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 3 starts at:
 
 Initial Mass          90070.  lb.  (CL 0.27 trapezoidal)
 Initial Altitude      10000.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (fixed)
 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 = 15.0 mins, endmass = 88756.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:  +21839.   +673.   +78.21    +1313.7   +19.69   +0.037   +1.78
 Final :   31839.    900.    95.19     1982.6    32.77    0.051    2.53
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           10000.   226.8    16.97      668.9    7290.    300.   0.541   2941.  5855.   345.
           11149.   250.6    19.28      728.4    7102.    300.   0.552   2851.  5846.   351.
           12299.   275.2    21.70      788.4    6916.    300.   0.564   2760.  5837.   357.
           13448.   300.6    24.24      848.8    6732.    300.   0.576   2669.  5826.   363.
           14598.   326.9    26.92      909.8    6551.    300.   0.589   2576.  5815.   369.
           15747.   354.2    29.74      971.4    6370.    300.   0.601   2482.  5804.   376.
           16897.   382.5    32.72     1033.8    6204.    300.   0.614   2394.  5791.   382.
           18046.   411.8    35.86     1097.1    6039.    300.   0.628   2307.  5778.   389.
           19195.   442.3    39.18     1161.3    5877.    300.   0.641   2218.  5764.   395.
           20345.   474.1    42.69     1226.6    5718.    300.   0.656   2129.  5749.   402.
           21494.   507.2    46.42     1293.1    5561.    300.   0.670   2040.  5733.   409.
           22644.   541.7    50.39     1360.8    5407.    300.   0.685   1951.  5716.   416.
           23793.   577.9    54.61     1430.0    5255.    300.   0.700   1862.  5699.   424.
           24943.   615.9    59.12     1500.8    5107.    300.   0.716   1772.  5682.   431.
           26092.   655.9    63.96     1573.4    4958.    300.   0.732   1680.  5666.   439.
           27241.   698.1    69.15     1648.2    4813.    300.   0.749   1588.  5651.   447.
           28391.   743.0    74.76     1725.5    4672.    300.   0.766   1493.  5643.   455.
           29540.   790.8    80.86     1805.9    4535.    300.   0.783   1393.  5653.   463.
           30690.   842.6    87.57     1890.7    4399.    300.   0.801   1277.  5696.   471.
           31839.   900.2    95.19     1982.6    4265.    300.   0.820   1124.  5826.   479.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 4 starts at:
 
 Initial Mass          88756.  lb.  (CL 0.29 trapezoidal)
 Initial Altitude      31839.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (fixed Mach 0.820)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      4265.  lbf. (100% MCL) 

 Climb/Descent rate     1625.  feet/min 
 Flightpath angle        1.9   deg. (grad.3.35%)
 True airspeed           479.  kts

 Fuel Flow rate         5665.  lb/hr 
 NOx emission rate      73.3   lb/hr
 HC  emission rate     0.195   lb/hr
 CO  emission rate       9.6   lb/hr 

 L/D ratio             15.24
 Total aircraft drag    5826.  lbf. 

 Segment 4 ends at total time = 17.0 mins, endmass = 88572.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +3161.   +123.   +16.20     +184.0    +2.29   +0.007   +0.37
 Final :   35000.   1023.   111.39     2166.6    35.06    0.058    2.90
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           31839.   900.2    95.19     1982.6    4265.    300.   0.820   1625.  5826.   479.
           32005.   906.4    96.01     1992.3    4249.    299.   0.820   1618.  5803.   479.
           32172.   912.6    96.83     2001.9    4232.    298.   0.820   1611.  5780.   479.
           32338.   918.8    97.66     2011.6    4216.    297.   0.820   1603.  5758.   478.
           32505.   925.0    98.49     2021.2    4199.    296.   0.820   1596.  5735.   478.
           32671.   931.3    99.32     2030.9    4182.    295.   0.820   1588.  5713.   478.
           32837.   937.6   100.15     2040.6    4166.    293.   0.820   1580.  5691.   477.
           33004.   943.9   100.99     2050.2    4149.    292.   0.820   1572.  5670.   477.
           33170.   950.3   101.84     2059.9    4132.    291.   0.820   1564.  5649.   477.
           33336.   956.7   102.68     2069.6    4116.    290.   0.820   1556.  5628.   476.
           33503.   963.1   103.53     2079.2    4099.    289.   0.820   1547.  5607.   476.
           33669.   969.6   104.39     2088.9    4082.    288.   0.820   1539.  5586.   476.
           33835.   976.1   105.25     2098.6    4066.    287.   0.820   1530.  5566.   475.
           34002.   982.7   106.11     2108.3    4049.    286.   0.820   1521.  5546.   475.
           34168.   989.2   106.98     2118.0    4033.    285.   0.820   1512.  5526.   474.
           34335.   995.9   107.85     2127.7    4016.    284.   0.820   1503.  5506.   474.
           34501.   1003.   108.73     2137.4    3999.    283.   0.820   1494.  5487.   474.
           34667.   1009.   109.61     2147.1    3983.    282.   0.820   1484.  5468.   473.
           34834.   1016.   110.50     2156.9    3966.    281.   0.820   1475.  5449.   473.
           35000.   1023.   111.39     2166.6    3949.    279.   0.820   1465.  5431.   473.
 -----------------------------------------------------------------------------

 Acceleration to 299.kts in level flight at 35000.feet =0.03g:
 Time +51.1 sec, Dist +6.94 n.miles, Fuelburn +82.3 lb.
 NOx  +1.12 lb., HC +0.003 lb., CO +0.140 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 5 starts at:
 
 Initial Mass          88490.  lb.  (CL 0.29 trapezoidal)
 Initial Altitude      35000.  feet (1.66g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          299.  kts  (input Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3457.  lbf. (level cruise) =97.1%MCR

 Climb/Descent rate        0.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.00%)
 True airspeed           501.  kts

 Fuel Flow rate         4625.  lb/hr 
 NOx emission rate      50.9   lb/hr
 HC  emission rate     0.220   lb/hr
 CO  emission rate      14.8   lb/hr 

 L/D ratio             12.80
 Total aircraft drag    6913.  lbf. 

 Segment 5 ends at total time = 43.0 mins, endmass = 86561.lb.(1.69g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:      +0.  +1509.  +210.20    +1928.9   +21.13   +0.092   +6.28
 Final :   35000.   2583.   328.53     4177.8    57.31    0.153    9.32
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           35000.   1074.   118.33     2248.9    3457.    299.   0.870   0.     6913.   501.
           35000.   1153.   129.34     2350.4    3455.    299.   0.870   0.     6910.   501.
           35000.   1232.   140.36     2451.9    3453.    299.   0.870   0.     6906.   501.
           35000.   1311.   151.38     2553.5    3451.    299.   0.870   0.     6902.   501.
           35000.   1390.   162.41     2655.0    3449.    299.   0.870   0.     6899.   501.
           35000.   1470.   173.44     2756.5    3447.    299.   0.870   0.     6895.   501.
           35000.   1549.   184.48     2858.0    3446.    299.   0.870   0.     6891.   501.
           35000.   1628.   195.53     2959.6    3444.    299.   0.870   0.     6888.   501.
           35000.   1707.   206.58     3061.1    3442.    299.   0.870   0.     6884.   501.
           35000.   1787.   217.64     3162.6    3440.    299.   0.870   0.     6880.   501.
           35000.   1866.   228.70     3264.1    3438.    299.   0.870   0.     6877.   501.
           35000.   1946.   239.77     3365.7    3437.    299.   0.870   0.     6873.   501.
           35000.   2025.   250.84     3467.2    3435.    299.   0.870   0.     6869.   501.
           35000.   2105.   261.92     3568.7    3433.    299.   0.870   0.     6866.   501.
           35000.   2184.   273.01     3670.2    3431.    299.   0.870   0.     6862.   501.
           35000.   2264.   284.10     3771.7    3429.    299.   0.870   0.     6859.   501.
           35000.   2344.   295.20     3873.3    3428.    299.   0.870   0.     6855.   501.
           35000.   2423.   306.30     3974.8    3426.    299.   0.870   0.     6851.   501.
           35000.   2503.   317.41     4076.3    3424.    299.   0.870   0.     6848.   501.
           35000.   2583.   328.53     4177.8    3422.    299.   0.870   0.     6844.   501.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 6 starts at:
 
 Initial Mass          86561.  lb.  (CL 0.29 trapezoidal)
 Initial Altitude      35000.  feet (1.69g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          299.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3923.  lbf. (100% MCL) 

 Climb/Descent rate      654.  feet/min 
 Flightpath angle        0.7   deg. (grad.1.29%)
 True airspeed           501.  kts

 Fuel Flow rate         5252.  lb/hr 
 NOx emission rate      64.8   lb/hr
 HC  emission rate     0.199   lb/hr
 CO  emission rate      10.4   lb/hr 

 L/D ratio             12.65
 Total aircraft drag    6844.  lbf. 

 Segment 6 ends at total time = 46.9 mins, endmass = 86239.lb.(1.55g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +2000.   +231.   +32.12     +321.9    +3.82   +0.013   +0.74
 Final :   37000.   2814.   360.65     4499.7    61.13    0.167   10.06
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           35000.   2583.   328.53     4177.8    3923.    299.   0.870   654.   6844.   501.
           35105.   2593.   329.89     4192.0    3907.    298.   0.870   644.   6827.   501.
           35211.   2602.   331.26     4206.3    3891.    297.   0.870   634.   6810.   501.
           35316.   2612.   332.66     4220.8    3875.    297.   0.870   624.   6793.   501.
           35421.   2623.   334.08     4235.5    3859.    296.   0.870   613.   6776.   501.
           35526.   2633.   335.52     4250.3    3843.    295.   0.870   603.   6760.   500.
           35632.   2644.   336.99     4265.3    3827.    294.   0.870   593.   6743.   500.
           35737.   2654.   338.48     4280.5    3811.    294.   0.870   582.   6727.   500.
           35842.   2665.   340.00     4295.9    3795.    293.   0.870   572.   6711.   500.
           35947.   2677.   341.55     4311.6    3779.    292.   0.870   561.   6695.   499.
           36053.   2688.   343.13     4327.4    3763.    292.   0.870   550.   6679.   499.
           36158.   2700.   344.83     4344.4    3747.    291.   0.870   485.   6664.   499.
           36263.   2713.   346.65     4362.6    3731.    290.   0.870   475.   6649.   499.
           36368.   2727.   348.51     4381.1    3714.    289.   0.870   465.   6635.   499.
           36474.   2740.   350.42     4399.9    3698.    289.   0.870   455.   6620.   499.
           36579.   2755.   352.37     4419.1    3682.    288.   0.870   444.   6606.   499.
           36684.   2769.   354.36     4438.6    3666.    287.   0.870   434.   6592.   499.
           36789.   2784.   356.40     4458.6    3650.    287.   0.870   423.   6578.   499.
           36895.   2799.   358.50     4478.9    3634.    286.   0.870   413.   6564.   499.
           37000.   2814.   360.65     4499.7    3618.    285.   0.870   402.   6550.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 7 starts at:
 
 Initial Mass          86239.  lb.  (CL 0.32 trapezoidal)
 Initial Altitude      37000.  feet (1.55g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          285.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3275.  lbf. (level cruise) =99.8%MCR

 Climb/Descent rate        0.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.00%)
 True airspeed           499.  kts

 Fuel Flow rate         4356.  lb/hr 
 NOx emission rate      46.3   lb/hr
 HC  emission rate     0.221   lb/hr
 CO  emission rate      15.0   lb/hr 

 L/D ratio             13.17
 Total aircraft drag    6550.  lbf. 

 Segment 7 ends at total time = 154.3 mins, endmass = 78619.lb.(1.70g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:      +0.  +6443.  +893.09    +7619.8   +79.58   +0.400  +27.88
 Final :   37000.   9257.  1253.74    12119.5   140.71    0.567   37.94
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           37000.   2814.   360.65     4499.7    3275.    285.   0.870   0.     6550.   499.
           37000.   3146.   406.64     4900.7    3267.    285.   0.870   0.     6534.   499.
           37000.   3479.   452.75     5301.8    3259.    285.   0.870   0.     6518.   499.
           37000.   3812.   498.98     5702.8    3251.    285.   0.870   0.     6502.   499.
           37000.   4146.   545.31     6103.9    3243.    285.   0.870   0.     6486.   499.
           37000.   4482.   591.76     6504.9    3235.    285.   0.870   0.     6471.   499.
           37000.   4817.   638.32     6906.0    3228.    285.   0.870   0.     6455.   499.
           37000.   5154.   684.99     7307.0    3220.    285.   0.870   0.     6440.   499.
           37000.   5492.   731.78     7708.1    3212.    285.   0.870   0.     6424.   499.
           37000.   5830.   778.68     8109.1    3205.    285.   0.870   0.     6409.   499.
           37000.   6169.   825.69     8510.1    3197.    285.   0.870   0.     6394.   499.
           37000.   6509.   872.81     8911.2    3190.    285.   0.870   0.     6379.   499.
           37000.   6850.   920.04     9312.2    3182.    285.   0.870   0.     6364.   499.
           37000.   7191.   967.38     9713.3    3175.    285.   0.870   0.     6350.   499.
           37000.   7534.  1014.83    10114.3    3167.    285.   0.870   0.     6335.   499.
           37000.   7877.  1062.39    10515.4    3160.    285.   0.870   0.     6320.   499.
           37000.   8221.  1110.06    10916.4    3153.    285.   0.870   0.     6306.   499.
           37000.   8565.  1157.85    11317.5    3146.    285.   0.870   0.     6292.   499.
           37000.   8911.  1205.74    11718.5    3139.    285.   0.870   0.     6277.   499.
           37000.   9257.  1253.74    12119.5    3132.    285.   0.870   0.     6263.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 8 starts at:
 
 Initial Mass          78619.  lb.  (CL 0.29 trapezoidal)
 Initial Altitude      37000.  feet (1.70g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          285.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3618.  lbf. (100% MCL) 

 Climb/Descent rate      626.  feet/min 
 Flightpath angle        0.7   deg. (grad.1.24%)
 True airspeed           499.  kts

 Fuel Flow rate         4815.  lb/hr 
 NOx emission rate      55.9   lb/hr
 HC  emission rate     0.207   lb/hr
 CO  emission rate      11.7   lb/hr 

 L/D ratio             12.55
 Total aircraft drag    6263.  lbf. 

 Segment 8 ends at total time = 158.2 mins, endmass = 78319.lb.(1.55g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +2000.   +235.   +32.58     +300.2    +3.41   +0.013   +0.75
 Final :   39000.   9492.  1286.32    12419.7   144.13    0.580   38.69
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           37000.   9257.  1253.74    12119.5    3618.    285.   0.870   626.   6263.   499.
           37105.   9267.  1255.15    12133.1    3602.    285.   0.870   615.   6248.   499.
           37211.   9278.  1256.58    12146.9    3586.    284.   0.870   604.   6233.   499.
           37316.   9288.  1258.05    12160.9    3570.    283.   0.870   593.   6218.   499.
           37421.   9299.  1259.54    12175.0    3554.    283.   0.870   582.   6203.   499.
           37526.   9310.  1261.05    12189.4    3538.    282.   0.870   571.   6188.   499.
           37632.   9321.  1262.60    12203.9    3522.    281.   0.870   560.   6174.   499.
           37737.   9333.  1264.18    12218.7    3506.    280.   0.870   549.   6159.   499.
           37842.   9344.  1265.79    12233.8    3490.    280.   0.870   537.   6145.   499.
           37947.   9356.  1267.44    12249.1    3474.    279.   0.870   526.   6131.   499.
           38053.   9368.  1269.12    12264.6    3458.    278.   0.870   514.   6117.   499.
           38158.   9381.  1270.85    12280.5    3442.    278.   0.870   503.   6103.   499.
           38263.   9393.  1272.61    12296.6    3426.    277.   0.870   491.   6090.   499.
           38368.   9406.  1274.42    12313.1    3410.    276.   0.870   479.   6076.   499.
           38474.   9420.  1276.27    12329.9    3394.    276.   0.870   467.   6063.   499.
           38579.   9433.  1278.17    12347.0    3378.    275.   0.870   455.   6050.   499.
           38684.   9447.  1280.12    12364.5    3362.    274.   0.870   443.   6037.   499.
           38789.   9462.  1282.13    12382.5    3345.    274.   0.870   430.   6024.   499.
           38895.   9477.  1284.19    12400.9    3329.    273.   0.870   418.   6011.   499.
           39000.   9492.  1286.32    12419.7    3313.    272.   0.870   405.   5998.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 9 starts at:
 
 Initial Mass          78319.  lb.  (CL 0.32 trapezoidal)
 Initial Altitude      39000.  feet (1.55g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          272.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2999.  lbf. (level cruise) =99.8%MCR

 Climb/Descent rate        0.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.00%)
 True airspeed           499.  kts

 Fuel Flow rate         3990.  lb/hr 
 NOx emission rate      40.7   lb/hr
 HC  emission rate     0.221   lb/hr
 CO  emission rate      14.8   lb/hr 

 L/D ratio             13.06
 Total aircraft drag    5998.  lbf. 

 Segment 9 ends at total time = 274.0 mins, endmass = 70806.lb.(1.71g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:      +0.  +6949.  +963.30    +7513.8   +75.09   +0.431  +29.82
 Final :   39000.  16442.  2249.62    19933.5   219.22    1.012   68.51
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           39000.   9492.  1286.32    12419.7    2999.    272.   0.870   0.     5998.   499.
           39000.   9850.  1335.85    12815.2    2991.    272.   0.870   0.     5982.   499.
           39000.  10208.  1385.51    13210.6    2983.    272.   0.870   0.     5967.   499.
           39000.  10567.  1435.31    13606.1    2976.    272.   0.870   0.     5951.   499.
           39000.  10927.  1485.23    14001.5    2968.    272.   0.870   0.     5935.   499.
           39000.  11288.  1535.29    14397.0    2960.    272.   0.870   0.     5920.   499.
           39000.  11650.  1585.48    14792.5    2952.    272.   0.870   0.     5905.   499.
           39000.  12013.  1635.80    15187.9    2945.    272.   0.870   0.     5890.   499.
           39000.  12377.  1686.24    15583.4    2937.    272.   0.870   0.     5875.   499.
           39000.  12742.  1736.82    15978.9    2930.    272.   0.870   0.     5860.   499.
           39000.  13108.  1787.53    16374.3    2922.    272.   0.870   0.     5845.   499.
           39000.  13475.  1838.36    16769.8    2915.    272.   0.870   0.     5830.   499.
           39000.  13842.  1889.32    17165.2    2908.    272.   0.870   0.     5816.   499.
           39000.  14211.  1940.41    17560.7    2901.    272.   0.870   0.     5801.   499.
           39000.  14580.  1991.63    17956.2    2893.    272.   0.870   0.     5787.   499.
           39000.  14951.  2042.98    18351.6    2886.    272.   0.870   0.     5773.   499.
           39000.  15322.  2094.45    18747.1    2879.    272.   0.870   0.     5759.   499.
           39000.  15694.  2146.04    19142.5    2872.    272.   0.870   0.     5745.   499.
           39000.  16068.  2197.77    19538.0    2865.    272.   0.870   0.     5731.   499.
           39000.  16442.  2249.62    19933.5    2858.    272.   0.870   0.     5717.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 10 starts at:
 
 Initial Mass          70806.  lb.  (CL 0.29 trapezoidal)
 Initial Altitude      39000.  feet (1.71g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          272.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3313.  lbf. (100% MCL) 

 Climb/Descent rate      649.  feet/min 
 Flightpath angle        0.7   deg. (grad.1.28%)
 True airspeed           499.  kts

 Fuel Flow rate         4409.  lb/hr 
 NOx emission rate      49.1   lb/hr
 HC  emission rate     0.205   lb/hr
 CO  emission rate      11.4   lb/hr 

 L/D ratio             12.39
 Total aircraft drag    5717.  lbf. 

 Segment 10 ends at total time = 277.9 mins, endmass = 70536.lb.(1.56g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +2000.   +231.   +32.00     +269.1    +2.93   +0.013   +0.73
 Final :   41000.  16672.  2281.61    20202.5   222.14    1.025   69.24
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           39000.  16442.  2249.62    19933.5    3313.    272.   0.870   649.   5717.   499.
           39105.  16451.  2250.98    19945.5    3297.    272.   0.870   637.   5703.   499.
           39211.  16461.  2252.37    19957.7    3281.    271.   0.870   624.   5689.   499.
           39316.  16472.  2253.78    19970.0    3265.    270.   0.870   611.   5675.   499.
           39421.  16482.  2255.23    19982.6    3249.    270.   0.870   598.   5661.   499.
           39526.  16493.  2256.71    19995.4    3233.    269.   0.870   585.   5647.   499.
           39632.  16504.  2258.23    20008.4    3217.    269.   0.870   572.   5634.   499.
           39737.  16515.  2259.77    20021.7    3201.    268.   0.870   559.   5620.   499.
           39842.  16526.  2261.36    20035.2    3185.    267.   0.870   545.   5607.   499.
           39947.  16538.  2262.99    20048.9    3169.    267.   0.870   532.   5594.   499.
           40053.  16550.  2264.65    20063.0    3154.    266.   0.870   520.   5581.   499.
           40158.  16562.  2266.35    20077.3    3139.    265.   0.870   508.   5568.   499.
           40263.  16575.  2268.10    20091.8    3125.    265.   0.870   496.   5555.   499.
           40368.  16588.  2269.88    20106.7    3110.    264.   0.870   485.   5542.   499.
           40474.  16601.  2271.71    20121.8    3095.    263.   0.870   473.   5530.   499.
           40579.  16614.  2273.59    20137.2    3081.    263.   0.870   461.   5518.   499.
           40684.  16628.  2275.51    20153.0    3066.    262.   0.870   449.   5506.   499.
           40789.  16643.  2277.49    20169.1    3052.    261.   0.870   437.   5493.   499.
           40895.  16657.  2279.52    20185.6    3037.    261.   0.870   425.   5482.   499.
           41000.  16672.  2281.61    20202.5    3023.    260.   0.870   412.   5470.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 11 starts at:
 
 Initial Mass          70536.  lb.  (CL 0.31 trapezoidal)
 Initial Altitude      41000.  feet (1.56g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          260.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2735.  lbf. (level cruise) =99.8%MCR

 Climb/Descent rate        0.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.00%)
 True airspeed           499.  kts

 Fuel Flow rate         3638.  lb/hr 
 NOx emission rate      35.4   lb/hr
 HC  emission rate     0.221   lb/hr
 CO  emission rate      14.7   lb/hr 

 L/D ratio             12.90
 Total aircraft drag    5470.  lbf. 

 Segment 11 ends at total time = 403.1 mins, endmass = 63143.lb.(1.74g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:      +0.  +7511. +1041.11    +7393.9   +70.48   +0.467  +32.16
 Final :   41000.  24183.  3322.72    27596.5   292.63    1.491  101.40
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           41000.  16672.  2281.61    20202.5    2735.    260.   0.870   0.     5470.   499.
           41000.  17058.  2335.07    20591.7    2727.    260.   0.870   0.     5454.   499.
           41000.  17445.  2388.68    20980.9    2720.    260.   0.870   0.     5439.   499.
           41000.  17833.  2442.44    21370.0    2712.    260.   0.870   0.     5424.   499.
           41000.  18221.  2496.35    21759.2    2704.    260.   0.870   0.     5409.   499.
           41000.  18611.  2550.41    22148.3    2697.    260.   0.870   0.     5394.   499.
           41000.  19003.  2604.61    22537.5    2690.    260.   0.870   0.     5379.   499.
           41000.  19395.  2658.97    22926.6    2682.    260.   0.870   0.     5364.   499.
           41000.  19788.  2713.48    23315.8    2675.    260.   0.870   0.     5350.   499.
           41000.  20182.  2768.13    23704.9    2668.    260.   0.870   0.     5336.   499.
           41000.  20578.  2822.94    24094.1    2661.    260.   0.870   0.     5321.   499.
           41000.  20974.  2877.89    24483.2    2654.    260.   0.870   0.     5307.   499.
           41000.  21371.  2932.98    24872.4    2647.    260.   0.870   0.     5293.   499.
           41000.  21770.  2988.22    25261.6    2640.    260.   0.870   0.     5279.   499.
           41000.  22170.  3043.61    25650.7    2633.    260.   0.870   0.     5265.   499.
           41000.  22570.  3099.15    26039.9    2626.    260.   0.870   0.     5252.   499.
           41000.  22972.  3154.83    26429.0    2619.    260.   0.870   0.     5238.   499.
           41000.  23375.  3210.65    26818.2    2612.    260.   0.870   0.     5225.   499.
           41000.  23778.  3266.61    27207.3    2606.    260.   0.870   0.     5211.   499.
           41000.  24183.  3322.72    27596.5    2599.    260.   0.870   0.     5198.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 12 starts at:
 
 Initial Mass          63143.  lb.  (CL 0.28 trapezoidal)
 Initial Altitude      41000.  feet (1.74g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          260.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      3023.  lbf. (100% MCL) 

 Climb/Descent rate      678.  feet/min 
 Flightpath angle        0.8   deg. (grad.1.34%)
 True airspeed           499.  kts

 Fuel Flow rate         4022.  lb/hr 
 NOx emission rate      42.9   lb/hr
 HC  emission rate     0.205   lb/hr
 CO  emission rate      11.2   lb/hr 

 L/D ratio             12.15
 Total aircraft drag    5198.  lbf. 

 Segment 12 ends at total time = 406.7 mins, endmass = 62908.lb.(1.59g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +2000.   +221.   +30.60     +234.5    +2.44   +0.013   +0.69
 Final :   43000.  24404.  3353.32    27830.9   295.06    1.504  102.08
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           41000.  24183.  3322.72    27596.5    3023.    260.   0.870   678.   5198.   499.
           41105.  24192.  3324.03    27607.0    3008.    260.   0.870   665.   5185.   499.
           41211.  24202.  3325.36    27617.6    2993.    259.   0.870   653.   5172.   499.
           41316.  24212.  3326.71    27628.4    2979.    258.   0.870   640.   5158.   499.
           41421.  24222.  3328.09    27639.3    2964.    258.   0.870   627.   5145.   499.
           41526.  24232.  3329.50    27650.4    2950.    257.   0.870   614.   5133.   499.
           41632.  24242.  3330.94    27661.7    2935.    256.   0.870   601.   5120.   499.
           41737.  24253.  3332.41    27673.2    2921.    256.   0.870   588.   5107.   499.
           41842.  24264.  3333.92    27684.9    2906.    255.   0.870   575.   5095.   499.
           41947.  24275.  3335.46    27696.8    2892.    255.   0.870   562.   5082.   499.
           42053.  24286.  3337.04    27709.0    2877.    254.   0.870   548.   5070.   499.
           42158.  24298.  3338.65    27721.3    2862.    253.   0.870   535.   5058.   499.
           42263.  24310.  3340.31    27734.0    2848.    253.   0.870   521.   5046.   499.
           42368.  24322.  3342.01    27746.9    2833.    252.   0.870   508.   5034.   499.
           42474.  24335.  3343.76    27760.0    2819.    251.   0.870   494.   5022.   499.
           42579.  24348.  3345.56    27773.5    2804.    251.   0.870   480.   5010.   499.
           42684.  24361.  3347.41    27787.3    2790.    250.   0.870   466.   4999.   499.
           42789.  24375.  3349.32    27801.5    2775.    250.   0.870   452.   4987.   499.
           42895.  24389.  3351.29    27816.0    2761.    249.   0.870   438.   4976.   499.
           43000.  24404.  3353.32    27830.9    2746.    248.   0.870   423.   4965.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 13 starts at:
 
 Initial Mass          62908.  lb.  (CL 0.31 trapezoidal)
 Initial Altitude      43000.  feet (1.59g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          248.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2482.  lbf. (level cruise) =99.8%MCR

 Climb/Descent rate        0.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.00%)
 True airspeed           499.  kts

 Fuel Flow rate         3302.  lb/hr 
 NOx emission rate      30.6   lb/hr
 HC  emission rate     0.221   lb/hr
 CO  emission rate      14.8   lb/hr 

 L/D ratio             12.67
 Total aircraft drag    4965.  lbf. 

 Segment 13 ends at total time = 553.9 mins, endmass = 55043.lb.(1.81g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:      +0.  +8832. +1224.29    +7865.1   +71.15   +0.551  +38.14
 Final :   43000.  33236.  4577.61    35696.0   366.22    2.054  140.23
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           43000.  24404.  3353.32    27830.9    2482.    248.   0.870   0.     4965.   499.
           43000.  24856.  3415.98    28244.9    2474.    248.   0.870   0.     4949.   499.
           43000.  25309.  3478.84    28658.8    2467.    248.   0.870   0.     4933.   499.
           43000.  25764.  3541.90    29072.8    2459.    248.   0.870   0.     4918.   499.
           43000.  26221.  3605.16    29486.7    2451.    248.   0.870   0.     4902.   499.
           43000.  26678.  3668.62    29900.7    2443.    248.   0.870   0.     4887.   499.
           43000.  27138.  3732.28    30314.7    2436.    248.   0.870   0.     4872.   499.
           43000.  27598.  3796.14    30728.6    2428.    248.   0.870   0.     4857.   499.
           43000.  28060.  3860.20    31142.6    2421.    248.   0.870   0.     4842.   499.
           43000.  28524.  3924.45    31556.5    2414.    248.   0.870   0.     4827.   499.
           43000.  28989.  3988.90    31970.5    2406.    248.   0.870   0.     4812.   499.
           43000.  29455.  4053.54    32384.4    2399.    248.   0.870   0.     4798.   499.
           43000.  29923.  4118.38    32798.4    2392.    248.   0.870   0.     4784.   499.
           43000.  30392.  4183.41    33212.3    2385.    248.   0.870   0.     4770.   499.
           43000.  30863.  4248.63    33626.3    2378.    248.   0.870   0.     4756.   499.
           43000.  31334.  4314.04    34040.2    2371.    248.   0.870   0.     4742.   499.
           43000.  31808.  4379.65    34454.2    2364.    248.   0.870   0.     4728.   499.
           43000.  32282.  4445.45    34868.1    2357.    248.   0.870   0.     4715.   499.
           43000.  32758.  4511.43    35282.1    2351.    248.   0.870   0.     4701.   499.
           43000.  33236.  4577.61    35696.0    2344.    248.   0.870   0.     4688.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 14 starts at:
 
 Initial Mass          55043.  lb.  (CL 0.27 trapezoidal)
 Initial Altitude      43000.  feet (1.81g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          248.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2746.  lbf. (100% MCL) 

 Climb/Descent rate      738.  feet/min 
 Flightpath angle        0.8   deg. (grad.1.46%)
 True airspeed           499.  kts

 Fuel Flow rate         3654.  lb/hr 
 NOx emission rate      37.1   lb/hr
 HC  emission rate     0.205   lb/hr
 CO  emission rate      11.2   lb/hr 

 L/D ratio             11.74
 Total aircraft drag    4688.  lbf. 

 Segment 14 ends at total time = 557.4 mins, endmass = 54844.lb.(1.65g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:   +2000.   +208.   +28.77     +199.1    +1.96   +0.012   +0.66
 Final :   45000.  33443.  4606.37    35895.1   368.18    2.066  140.89
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           43000.  33236.  4577.61    35696.0    2746.    248.   0.870   738.   4688.   499.
           43105.  33244.  4578.81    35704.8    2731.    248.   0.870   723.   4675.   499.
           43211.  33253.  4580.03    35713.7    2717.    247.   0.870   708.   4662.   499.
           43316.  33262.  4581.28    35722.7    2702.    247.   0.870   693.   4650.   499.
           43421.  33271.  4582.56    35731.9    2688.    246.   0.870   678.   4637.   499.
           43526.  33281.  4583.86    35741.2    2673.    245.   0.870   663.   4625.   499.
           43632.  33291.  4585.20    35750.7    2659.    245.   0.870   647.   4613.   499.
           43737.  33300.  4586.57    35760.4    2644.    244.   0.870   632.   4601.   499.
           43842.  33311.  4587.97    35770.2    2629.    244.   0.870   616.   4588.   499.
           43947.  33321.  4589.41    35780.3    2615.    243.   0.870   601.   4577.   499.
           44053.  33332.  4590.89    35790.6    2600.    242.   0.870   585.   4565.   499.
           44158.  33342.  4592.40    35801.1    2586.    242.   0.870   569.   4553.   499.
           44263.  33354.  4593.97    35811.8    2571.    241.   0.870   553.   4541.   499.
           44368.  33365.  4595.57    35822.8    2557.    241.   0.870   537.   4530.   499.
           44474.  33377.  4597.23    35834.0    2542.    240.   0.870   521.   4518.   499.
           44579.  33390.  4598.94    35845.6    2528.    239.   0.870   505.   4507.   499.
           44684.  33402.  4600.70    35857.4    2513.    239.   0.870   488.   4496.   499.
           44789.  33415.  4602.52    35869.6    2498.    238.   0.870   472.   4485.   499.
           44895.  33429.  4604.41    35882.2    2484.    238.   0.870   455.   4474.   499.
           45000.  33443.  4606.37    35895.1    2469.    237.   0.870   439.   4463.   499.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 15 starts at:
 
 Initial Mass          54844.  lb.  (CL 0.30 trapezoidal)
 Initial Altitude      45000.  feet (1.65g buffet)
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          237.  kts  (fixed Mach 0.870)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine      2231.  lbf. (level cruise) =99.9%MCR

 Climb/Descent rate        0.  feet/min 
 Flightpath angle        0.0   deg. (grad.0.00%)
 True airspeed           499.  kts

 Fuel Flow rate         2968.  lb/hr 
 NOx emission rate      25.9   lb/hr
 HC  emission rate     0.223   lb/hr
 CO  emission rate      15.1   lb/hr 

 L/D ratio             12.29
 Total aircraft drag    4463.  lbf. 

 Segment 15 ends at total time = 591.5 mins, endmass = 53168.lb.(1.71g buff)

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:      +0.  +2046.  +283.65    +1675.6   +14.57   +0.127   +8.68
 Final :   45000.  35489.  4890.02    37570.7   382.74    2.193  149.57
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           45000.  33443.  4606.37    35895.1    2231.    237.   0.870   0.     4463.   499.
           45000.  33550.  4621.21    35983.3    2230.    237.   0.870   0.     4460.   499.
           45000.  33657.  4636.05    36071.5    2228.    237.   0.870   0.     4456.   499.
           45000.  33765.  4650.90    36159.7    2227.    237.   0.870   0.     4453.   499.
           45000.  33872.  4665.77    36247.9    2225.    237.   0.870   0.     4450.   499.
           45000.  33979.  4680.64    36336.1    2223.    237.   0.870   0.     4447.   499.
           45000.  34086.  4695.53    36424.3    2222.    237.   0.870   0.     4444.   499.
           45000.  34194.  4710.43    36512.4    2220.    237.   0.870   0.     4440.   499.
           45000.  34301.  4725.34    36600.6    2219.    237.   0.870   0.     4437.   499.
           45000.  34409.  4740.25    36688.8    2217.    237.   0.870   0.     4434.   499.
           45000.  34517.  4755.18    36777.0    2215.    237.   0.870   0.     4431.   499.
           45000.  34625.  4770.12    36865.2    2214.    237.   0.870   0.     4428.   499.
           45000.  34732.  4785.07    36953.4    2212.    237.   0.870   0.     4425.   499.
           45000.  34840.  4800.03    37041.6    2211.    237.   0.870   0.     4422.   499.
           45000.  34948.  4815.00    37129.8    2209.    237.   0.870   0.     4419.   499.
           45000.  35056.  4829.99    37218.0    2208.    237.   0.870   0.     4415.   499.
           45000.  35165.  4844.98    37306.2    2206.    237.   0.870   0.     4412.   499.
           45000.  35273.  4859.98    37394.3    2205.    237.   0.870   0.     4409.   499.
           45000.  35381.  4874.99    37482.5    2203.    237.   0.870   0.     4406.   499.
           45000.  35489.  4890.02    37570.7    2202.    237.   0.870   0.     4403.   499.
 -----------------------------------------------------------------------------

 Deceleration to 222.kts in level flight at 45000.feet =-0.06g:
 Time +27.3 sec, Dist +3.67 n.miles, Fuelburn +6.9 lb.
 NOx  +0.03 lb., HC +0.011 lb., CO +0.307 lb.

 -----------------------------------------------------------------------------
 Manoeuvre segment 16 starts at:
 
 Initial Mass          53161.  lb.  (CL 0.32 trapezoidal)
 Initial Altitude      45000.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          222.  kts  (input Mach 0.820)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine       458.  lbf. (idle) 

 Climb/Descent rate    -2292.  feet/min 
 Flightpath angle       -2.8   deg. (grad.-4.81%)
 True airspeed           470.  kts

 Fuel Flow rate          904.  lb/hr 
 NOx emission rate       3.8   lb/hr
 HC  emission rate     1.437   lb/hr
 CO  emission rate      41.1   lb/hr 

 L/D ratio             15.30
 Total aircraft drag    3474.  lbf. 

 Segment 16 ends at total time = 596.0 mins, endmass = 53103.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:  -13161.   +245.   +32.04      +58.8    +0.24   +0.109   +2.88
 Final :   31839.  35762.  4925.73    37636.4   383.01    2.313  152.75
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           45000.  35517.  4893.69    37577.6    458.     222.   0.820   -2292. 3474.   470.
           44307.  35535.  4896.02    37582.1    442.     225.   0.820   -2367. 3526.   470.
           43615.  35552.  4898.28    37586.4    426.     229.   0.820   -2445. 3580.   470.
           42922.  35569.  4900.46    37590.5    410.     233.   0.820   -2525. 3638.   470.
           42229.  35585.  4902.58    37594.5    394.     236.   0.820   -2609. 3699.   470.
           41537.  35600.  4904.63    37598.4    378.     240.   0.820   -2695. 3763.   470.
           40844.  35616.  4906.61    37602.1    362.     244.   0.820   -2784. 3830.   470.
           40151.  35630.  4908.53    37605.7    346.     248.   0.820   -2876. 3900.   470.
           39459.  35645.  4910.38    37609.1    317.     252.   0.820   -2994. 3974.   470.
           38766.  35658.  4912.16    37612.4    284.     256.   0.820   -3122. 4051.   470.
           38073.  35671.  4913.86    37615.5    251.     260.   0.820   -3254. 4131.   470.
           37381.  35684.  4915.50    37618.5    218.     265.   0.820   -3388. 4215.   470.
           36688.  35696.  4917.07    37621.3    185.     269.   0.820   -3526. 4302.   470.
           35995.  35707.  4918.51    37623.9    153.     273.   0.820   -4029. 4394.   471.
           35302.  35717.  4919.84    37626.3    120.     278.   0.820   -4205. 4493.   472.
           34610.  35727.  4921.11    37628.5    87.      282.   0.820   -4387. 4597.   474.
           33917.  35736.  4922.33    37630.6    54.      286.   0.820   -4573. 4704.   475.
           33224.  35745.  4923.51    37632.6    21.      291.   0.820   -4763. 4815.   476.
           32532.  35753.  4924.64    37634.5    -12.     295.   0.820   -4958. 4929.   478.
           31839.  35762.  4925.73    37636.4    -45.     300.   0.820   -5158. 5047.   479.
 -----------------------------------------------------------------------------

 -----------------------------------------------------------------------------
 Manoeuvre segment 17 starts at:
 
 Initial Mass          53103.  lb.  (CL 0.17 trapezoidal)
 Initial Altitude      31839.  feet 
 Delta-ISA                +0.  deg.C
 Airspeed (CAS)          300.  kts  (fixed)
 Flaps                     0   deg. (hi-speed)
 Undercarriage            up
 All eng.operative
 Thrust per engine       -45.  lbf. (idle) 

 Climb/Descent rate    -3570.  feet/min 
 Flightpath angle       -4.2   deg. (grad.-7.35%)
 True airspeed           479.  kts

 Fuel Flow rate          798.  lb/hr 
 NOx emission rate       3.2   lb/hr
 HC  emission rate     1.520   lb/hr
 CO  emission rate      38.6   lb/hr 

 L/D ratio             10.52
 Total aircraft drag    5047.  lbf. 

 Segment 17 ends at total time = 602.2 mins, endmass = 53027.lb.

         Altitude   Time   Distance   Fuel Burn    NOx     HC      CO
           feet      sec    n.miles     lb.        lb.     lb.     lb.
 
 Increm:  -21839.   +371.   +42.06      +76.0    +0.29   +0.136   +3.40
 Final :   10000.  36133.  4967.79    37712.4   383.30    2.449  156.15
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           31839.  35762.  4925.73    37636.4    -45.     300.   0.820   -3570. 5047.   479.
           30690.  35781.  4928.30    37640.7    -73.     300.   0.801   -3510. 4949.   471.
           29540.  35801.  4930.86    37645.0    -101.    300.   0.783   -3489. 4908.   463.
           28391.  35821.  4933.38    37649.3    -117.    300.   0.766   -3475. 4901.   455.
           27241.  35840.  4935.87    37653.7    -139.    300.   0.749   -3479. 4911.   447.
           26092.  35860.  4938.30    37658.0    -167.    300.   0.732   -3494. 4928.   439.
           24943.  35880.  4940.67    37662.2    -200.    300.   0.716   -3516. 4946.   431.
           23793.  35899.  4942.99    37666.3    -238.    300.   0.700   -3544. 4964.   424.
           22644.  35919.  4945.26    37670.2    -262.    300.   0.685   -3551. 4984.   416.
           21494.  35938.  4947.49    37674.1    -284.    300.   0.670   -3555. 5002.   409.
           20345.  35958.  4949.67    37677.9    -306.    300.   0.656   -3557. 5019.   402.
           19195.  35977.  4951.82    37681.7    -325.    300.   0.641   -3555. 5036.   395.
           18046.  35996.  4953.93    37685.6    -349.    300.   0.628   -3556. 5051.   389.
           16897.  36016.  4956.01    37689.4    -377.    300.   0.614   -3561. 5065.   382.
           15747.  36035.  4958.04    37693.2    -409.    300.   0.601   -3569. 5079.   376.
           14598.  36054.  4960.04    37696.9    -430.    300.   0.589   -3563. 5091.   369.
           13448.  36074.  4962.02    37700.7    -447.    300.   0.576   -3551. 5103.   363.
           12299.  36093.  4963.96    37704.5    -461.    300.   0.564   -3534. 5114.   357.
           11149.  36113.  4965.89    37708.4    -472.    300.   0.552   -3514. 5124.   351.
           10000.  36133.  4967.79    37712.4    -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 18 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 18 ends at total time = 606.6 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.  36399.  4988.20    37778.2   383.57    2.543  158.51
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
           10000.  36162.  4970.42    37718.7    -298.    250.   0.452   -2274. 3979.   289.
            9553.  36174.  4971.36    37721.2    -298.    250.   0.449   -2264. 3980.   287.
            9105.  36186.  4972.30    37723.8    -299.    250.   0.445   -2253. 3980.   285.
            8658.  36198.  4973.25    37726.5    -298.    250.   0.441   -2242. 3981.   283.
            8211.  36210.  4974.19    37729.2    -298.    250.   0.438   -2231. 3982.   281.
            7763.  36222.  4975.13    37732.0    -297.    250.   0.434   -2219. 3983.   279.
            7316.  36234.  4976.06    37734.9    -296.    250.   0.431   -2207. 3984.   278.
            6868.  36247.  4977.00    37737.8    -295.    250.   0.427   -2195. 3984.   276.
            6421.  36259.  4977.94    37740.8    -294.    250.   0.424   -2183. 3985.   274.
            5974.  36271.  4978.87    37743.8    -292.    250.   0.420   -2171. 3985.   272.
            5526.  36284.  4979.81    37746.9    -290.    250.   0.417   -2158. 3986.   270.
            5079.  36296.  4980.74    37750.1    -288.    250.   0.413   -2146. 3987.   269.
            4632.  36309.  4981.68    37753.4    -286.    250.   0.410   -2133. 3987.   267.
            4184.  36321.  4982.61    37756.7    -283.    250.   0.407   -2120. 3987.   265.
            3737.  36334.  4983.54    37760.1    -281.    250.   0.404   -2107. 3988.   264.
            3289.  36347.  4984.47    37763.5    -278.    250.   0.400   -2093. 3988.   262.
            2842.  36360.  4985.41    37767.1    -275.    250.   0.397   -2081. 3988.   260.
            2395.  36372.  4986.34    37770.7    -273.    250.   0.394   -2068. 3989.   259.
            1947.  36385.  4987.27    37774.4    -271.    250.   0.391   -2056. 3989.   257.
            1500.  36399.  4988.20    37778.2    -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 19 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      2113.  lbf. (match grad.) =18.9%MCL

 Climb/Descent rate     -602.  feet/min 
 Flightpath angle       -3.0   deg. (grad.-5.24%)
 True airspeed           114.  kts

 Fuel Flow rate         3327.  lb/hr 
 NOx emission rate      25.7   lb/hr
 HC  emission rate     0.170   lb/hr
 CO  emission rate      16.2   lb/hr 

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

 Segment 19 ends at total time = 609.6 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     +137.0    +1.06   +0.007   +0.66
 Final :      50.  36576.  4989.68    37925.0   384.67    2.562  159.48
 -----------------------------------------------------------------------------
 History:    Alt    Time      Dist      Burnt    FN/eng   CAS    Mach    RoC    Drag    TAS
            1500.  36430.    0.000    37788.0    2113.    111.   0.173   -602.  7046.   114.
            1339.  36446.    0.000    37802.8    2113.    111.   0.172   -601.  7044.   113.
            1178.  36463.    0.000    37817.8    2113.    111.   0.172   -599.  7042.   113.
            1017.  36479.    0.000    37832.8    2112.    111.   0.171   -598.  7040.   113.
             856.  36495.    0.000    37848.0    2112.    111.   0.171   -596.  7038.   112.
             694.  36511.    0.000    37863.2    2111.    111.   0.170   -595.  7037.   112.
             533.  36527.    0.000    37878.5    2111.    111.   0.170   -593.  7035.   112.
             372.  36544.    0.000    37893.9    2111.    111.   0.169   -592.  7033.   112.
             211.  36560.    0.000    37909.4    2110.    111.   0.168   -591.  7031.   111.
              50.  36576.    0.000    37925.0    2110.    111.   0.168   -589.  7029.   111.
 -----------------------------------------------------------------------------
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