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Fokker F70 Sample Analysis

This sample text output was compiled directly from the Piano model of the Fokker F70. Various reports are shown, in no particular order.

>      Welcome to Piano Version 3.6!

>      Loading "Fokker F70 option"...
>      Loading "Medium-BPR Fan late80s" engine...
>      calculating geometry/mass/balance ...

>      Fokker F70 option ____________________________

>      PAYLOAD         79.  PAX = 15800.lb.

>      MTOW         84000.  lb.
>      OEW          49984.  lb. = 59.5% of mtow

>      FUEL-CAP.     3531.  US.gal. Avail/Req=1.29

>      SPAN          91.9   feet

>      WING-AREA     1006.  sq.feet trapezoidal

>      ENG.THRUST   13850.  *2 lbf. reference fn*
>                   13642.  *2 lbf. available slst

>      W/S             83.  p.s.f. trapezoidal

>      T/W          0.330   reference
>                   0.325   available
>      ______________________________________________

>      GEOMETRY REPORT
>      _______________
>                                     Wing    Stabiliser   Fin (excl.dorsal)
>                                     ----    ----------   ---
>      Area, trapezoidal reference   1006.43   244.47    178.83    sq.feet
>      Area, piano gross             1008.99   244.47    178.83    sq.feet
>      Area, airbus gross            997.60                        sq.feet
>      Area, boeing wimpress         1006.43                       sq.feet
>      Area, esdu                    1006.43                       sq.feet
>      Area, exposed                 821.77    244.47    178.83    sq.feet
>      Area, wetted                  1676.69   497.20    363.44    sq.feet

>      Aspect Ratio, trapezoidal       8.40      4.50      1.00
>      Aspect Ratio, piano gross       8.38      4.50      1.00
>      Aspect Ratio, airbus gross      8.47
>      Aspect Ratio, boeing wimpress   8.40
>      Aspect Ratio, esdu              8.40

>      Span                           91.95     33.17     13.37    feet

>      Sweepback at 1/4-chord         17.40     27.50     40.00    degrees

>      Taper Ratio (trapezoidal)       0.23      0.40      0.73

>      t/c at root                    0.123     0.104     0.102
>      t/c at thickness break           n/a
>      t/c at tip                     0.096     0.104     0.102

>      Volume Coefficient (V-bar)               0.925     0.073
>      Mean Aerodynamic Chord         12.41      7.82     13.48    feet
>      Arm between MAC 1/4 chords               47.22     37.62    feet

>      Wing chord at tip                                4.02       feet
>      Wing chord at planform break                      n/a       feet
>      Wing chord at root (gross)                      16.24       feet
>      Wing chord at c/line (gross)                    18.34       feet
>      Wing chord at c/line (notional trapezoidal)     17.87       feet

>      Planform break location        0.000  (fraction of exposed semispan)
>      Thickness break location       0.000  (fraction of exposed semispan)

>      Wing location (station of extended leading edge at c/line):
>      35.78 feet    (39.1 % of fuse.length)

>      Spar locations (fractions of local trapez.chord):
>      Wing root: 0.15, 0.65       Wing tip: 0.15, 0.65

>      Fuel capacity  avail/reqrd = 1.293
>      -------------  centresection is wet
>      Available:  3531.00 US.gal. (geometric capacity)
>      Required :  2731.03 US.gal. (at mtow & design payload)

>      Fuselage geometry
>      -----------------
>      fuselage max. width            10.83    feet
>      fuselage max. depth            10.83    feet

>      length, total fuselage         91.47    feet
>      length, front section          16.40    feet
>      length, mid section            35.37    feet
>      length, rear section           39.70    feet

>      wetted area, total fuselage   2587.85   sq.feet
>      wetted area, front section    416.91    sq.feet
>      wetted area, mid section      1202.05   sq.feet
>      wetted area, rear section     968.89    sq.feet

>      Nacelle geometry
>      ----------------
>      nacelle length                 16.08    feet
>      nacelle max. width              5.58    feet
>      nacelle max. depth              5.58    feet
>      wetted area per nac.          262.47    sq.feet

>      Overall dimensions
>      ------------------
>      Span                          91.95     feet
>      Overall aircraft length       101.25    feet
>      Height at top of fin          27.94     feet
>      Overall aircraft wetted area  5691.49   sq.feet

>      Design Limits
>      _____________

>      Design cruise point is Mach 0.77 at 32808.feet

>      Design dive Mach     MD       0.82
>      Design cruise speed  VC       327. KEAS
>      Design dive speed    VD       384. KEAS
>      Limit    load factor          3.16
>      Ultimate load factor          4.74
>      Cabin pressure differential   7.54 psi (limit)

>      Mass Report      (in lb. and % of MTOW)
>      ________________________________________

>      MTOW    84000.
>      OEW     49984.     (59.5%)
>      MZFW    72000.     (85.7%)
>      MLW     78999.     (94.0%)

>      Mass Breakdown            lb.    % MTOW
>      ________________________________________
>      wing group               8503.   10.12 %
>       (struct.box    6444.)
>       (flaps         1688.)
>       (spoilers       238.)
>       (ailerons       134.)
>      fuselage group           9527.   11.34 %
>      stabiliser               1095.    1.30 %
>      fin (incl.dorsal)        1003.    1.19 %
>      undercarriage            3247.    3.87 %
>      _____________________  _______   _______
>      basic structure total   23375.   27.83 %

>      powerplants total        7914.    9.42 %

>      furnishings              5608.    6.68 %
>      surface controls         1227.    1.46 %
>      fuel systems              562.    0.67 %
>      hydraulics                630.    0.75 %
>      electrics                1142.    1.36 %
>      avionics                  647.    0.77 %
>      APU                       573.    0.68 %
>      air conditioning          763.    0.91 %
>      misc. systems            2100.    2.50 %
>      _____________________  _______   _______
>      fixed equipment total   13252.   15.78 %

>      manufact. contingency       0.    0.00 %
>      _____________________  _______   _______
>      Manufact. Empty Mass    44541.   53.03 %  = MEW

>      crew                     1102.    1.31 %
>      operational items        4341.    5.17 %
>      _____________________  _______   _______
>      Operators Empty Mass    49984.   59.50 %  = OEW

>      design payload          15800.   18.81 %
>      design fuel             18216.   21.69 %
>      _____________________  _______   _______
>      Maximum Takeoff Mass    84000.   100   %  = MTOW

>      Calculating Design RangeÉÉDone.

>       RANGE REPORT
>       _____________

>       {Takeoff mass 84000.lb./ Fuel 18216.lb./ Payload 15800.lb.}

>       Range mode: fixed mach, step-up cruise, fixed climb sched.

>       Climb schedule: 250.kcas, 255.kcas, 0.650 mach

>       Cruise at Mach = 0.720  {FL 350}

>       ICA 35000.feet, 415.ktas, 242.kcas, CL=0.45, 2680.lbf./eng=MCR-9%
>       FCA 35000.feet, 415.ktas, 242.kcas, CL=0.39, 2486.lbf./eng=MCR-16%

>                     Distance        Time        Fuel
>                     (n.miles)      (min.)      (lb.)
>                     _________      ______     _______
>       Climb            134.          24.        2573.   {S.L to ICA}
>       Cruise          1158.         167.        9900.   {ICA to ICA}
>       Descent          129.          23.         623.   {ICA to S.L}
>                     _________      ______     _______
>       Trip  total     1420.         213.       13095.
>       Block total   =========       233.       13959.

>       Emissions: taxi,t/o  climb   cruise  descent  app,taxi   total
>       (lb.NOx)      2.7     30.4     62.3      1.8      1.9     99.1

>       Manoeuvre allowances:
>       taxi-out     214. lb. {extra to t/o mass}      9.min.
>       takeoff      169. lb.                          1.min.
>       approach     362. lb.                          5.min.
>       taxi-in      119. lb. {taken from reserves}    5.min.

>       Diversion distance          200. n.miles
>       Diversion mach            0.648
>       Diversion altitude        26061. feet
>       Diversion fuel             2184. lb.

>       Holding time                 45. minutes
>       Holding mach              0.258
>       Holding altitude           1500. feet
>       Holding fuel               2406. lb.

>       Contingency fuel              0. lb. {0.% of mission fuel}

>       Total Reserve fuel         4590. lb.

>      AERODYNAMIC DRAG REPORT at:
>      ---------------------------
>      MACH                  0.720
>      Altitude (pressure)   35000. feet
>      KTAS                  415.0
>      KEAS                  231.0
>      KCAS                  242.2
>      Reynolds number       1.723  millions per foot
>      Delta-ISA               +0.  deg.C.

>      CL                    0.440  based on:
>      Reference Area       1006.43 sq.feet  (trapezoidal)

>      Drag Coefficients based on ref.area
>      -----------------------------------

>      Cd Zero-Lift              0.01922    (65.9 %)
>      Cd Lift-Induced           0.00867    (29.7 %)
>      Cd Compressibility        0.00115    ( 4.0 %)
>      Cd Trim                   0.00013    ( 0.5 %)
>      Delta Cd (polar-mod)      0.00000    ( 0.0 %)
>                                -------    --------
>      Cd Total                  0.02917    ( 100 %)

>      Aerodynamic Boundaries:
>      -----------------------
>      Divergence Mach         0.737 {at the given CL 0.440}
>      Initial Buffet Mach     0.861 {at the given CL 0.440}
>      Initial Buffet CL       0.881 {at the given Mach 0.720}

>      Zero-Lift Component Breakdown (Drag Areas,= Cd*S = D/q)
>      -----------------------------

>      Wing                    5.901  sq.feet    (30.5 %)
>      Winglets                0.000  sq.feet    ( 0.0 %)
>      Fuselage & fairing      7.886  sq.feet    (40.8 %)
>      Stabiliser              1.862  sq.feet    ( 9.6 %)
>      Fin                     1.291  sq.feet    ( 6.7 %)  (incl.dorsal)
>      Nacelles (total)        2.403  sq.feet    (12.4 %)
>      User CdS Increment      0.000  sq.feet    ( 0.0 %)
>                            -------             --------
>      Total Cd0*S            19.342  sq.feet    ( 100 %)

>      Overall Lift / Drag Ratio = 15.08
>      =================================

>      Total Lift Force       80000. lbf.
>      Total Drag Force        5306. lbf. (2653.lbf. per engine)

>      Engine / Airframe Performance:
>      ------------------------------
>      Total Fuel Flow at Thrust=Drag:       3665. lb/hr
>      Specific Fuel Consumption (SFC)       0.6908 lb/hr/lbf
>      Specific Air Range (SAR)              0.1132 nm/lb
>      Emissions Index, NOx                  6.56 g/kg.
>      Available Total Thrust at MCR:        5901. lbf.
>      Available Total Thrust at MCL:        6394. lbf.

>      Instantaneous Performance Reserves at Weight=Lift:

>      RoC at MCR, constant Mach 0.720:      335. feet/min
>      RoC at MCR, constant 242.KCAS:        249. feet/min

>      RoC at MCL, constant Mach 0.720:      613. feet/min
>      RoC at MCL, constant 242.KCAS:        455. feet/min

>      Climb from 1500.feet to:   35000.feet
>      --------------------------------------------------
>      Time                22.72     minutes
>      Fuel burn           2461.     lb.
>      Distance            129.8     n.miles

>      Initial mass        84000.    lb.
>      Airspeed schedule   250.kcas, 255.kcas, 0.650 mach
>      Delta-ISA           +0.       deg.C.

>      NOx emissions       28.82     lb.
>      --------------------------------------------------

>      Climb details

>       Alt.     Time      Dist.      Burn      FN/eng    R.o.C.    NOx
>      (feet)    (sec)   (n.miles)    (lb.)     (lbf.)    (f.p.m)   (lb.)

>       1500.       0.       0.0         0.       7205.    2542.      0.0
>       2655.      28.       2.0        73.       7026.    2476.      1.1
>       3810.      56.       4.0       146.       6852.    2410.      2.1
>       4966.      85.       6.2       219.       6683.    2345.      3.1
>       6121.     115.       8.4       292.       6516.    2279.      4.1
>       7276.     146.      10.8       365.       6350.    2211.      5.2
>       8431.     178.      13.3       439.       6186.    2141.      6.2
>       9586.     211.      15.9       514.       6024.    2071.      7.1
>      10741.     249.      19.0       598.       5852.    1995.      8.3
>      11897.     284.      21.9       674.       5717.    1936.      9.2
>      13052.     320.      25.0       751.       5583.    1875.     10.2
>      14207.     358.      28.2       829.       5451.    1814.     11.2
>      15362.     397.      31.7       908.       5327.    1756.     12.2
>      16517.     437.      35.2       987.       5205.    1698.     13.2
>      17672.     479.      39.0      1067.       5084.    1638.     14.1
>      18828.     522.      43.0      1149.       4964.    1577.     15.1
>      19983.     567.      47.3      1232.       4845.    1515.     16.1
>      21138.     614.      51.8      1317.       4718.    1442.     17.1
>      22293.     663.      56.6      1404.       4596.    1368.     18.1
>      23448.     715.      61.8      1494.       4476.    1295.     19.1
>      24603.     770.      67.3      1587.       4363.    1224.     20.1
>      25759.     828.      73.4      1684.       4255.    1155.     21.2
>      26914.     890.      79.9      1784.       4150.    1087.     22.3
>      28069.     948.      86.0      1877.       4050.    1321.     23.3
>      29224.    1002.      91.8      1961.       3955.    1272.     24.1
>      30379.    1058.      97.8      2047.       3838.    1197.     25.0
>      31534.    1119.     104.3      2138.       3677.    1071.     25.9
>      32690.    1188.     111.5      2235.       3515.     941.     26.9
>      33845.    1268.     119.9      2341.       3354.     807.     27.8
>      35000.    1363.     129.8      2461.       3192.     668.     28.8

>      TAKEOFF PERFORMANCE {84000.lb., elevation 0.feet, ISA+0.deg.C.}
>      ___________________

>      JAR25 Takeoff Field Length     4919. feet

>      115% Factored All-Eng.Dist.    4820. feet
>      Balanced Field Length          4919. feet

>      2nd Segment Climb Gradient     5.59 %

>      Takeoff CLmax            1.91  {trapezoidal ref.area}
>      Takeoff Vstall           114.  keas
>      Takeoff Vfail            129.  keas
>      Takeoff V2               136.  keas
>      L/D at 2nd segment      12.54  {incl.windmill & asymm.}

>      Takeoff Wing Loading      83.  p.s.f.{trap.W/S}
>      Takeoff Thrust/Weight   0.325  available static

>      LANDING PERFORMANCE {78999.lb., elevation 0.feet, ISA+0.deg.C.}
>      ___________________

>      JAR25 Landing Field Length     4181. feet

>      Landing Distance (LFL*0.6)     2508. feet
>      Landing Ground Roll            1502. feet

>      Landing  CLmax           2.43  {trapezoidal ref.area}
>      Landing  Vstall           98.  keas
>      Approach Speed           127.  keas
>      Approach L/D             4.91  {gear down}

>      Iterating for Off-Design Range..Done.

>       RANGE REPORT
>       _____________

>       {Takeoff mass 75773.lb./ Fuel 9989.lb./ Payload 15800.lb.}

>       Range mode: fixed mach, step-up cruise, fixed climb sched.

>       Climb schedule: 250.kcas, 255.kcas, 0.650 mach

>       Cruise at Mach = 0.720  {FL 350}

>       ICA 35000.feet, 415.ktas, 242.kcas, CL=0.40, 2525.lbf./eng=MCR-14%
>       FCA 35000.feet, 415.ktas, 242.kcas, CL=0.39, 2484.lbf./eng=MCR-16%

>                     Distance        Time        Fuel
>                     (n.miles)      (min.)      (lb.)
>                     _________      ______     _______
>       Climb            110.          19.        2149.   {S.L to ICA}
>       Cruise           262.          38.        2179.   {ICA to ICA}
>       Descent          127.          22.         617.   {ICA to S.L}
>                     _________      ______     _______
>       Trip  total      500.          80.        4945.
>       Block total   =========       100.        5809.

>       Emissions: taxi,t/o  climb   cruise  descent  app,taxi   total
>       (lb.NOx)      2.7     25.5     13.2      1.7      1.9     45.1

>       Prices, millions of U.S.$
>       ________________________________

>       Airframe                  11.63
>       Engines                    3.08
>       Aircraft Delivery Price   14.71
>       ________________________________

>       Costing method: aea-89-medium-range

>       Operating Costs       U.S.$/trip    % of total
>       ______________________________________________

>       Depreciation              636.       11.79
>       Interest                  494.        9.14
>       Insurance                  43.        0.80

>       Flight Crew               845.       15.65
>       Cabin Crew                416.        7.70
>       Landing Fees              297.        5.50
>       Navigation                404.        7.49
>       Ground handling           717.       13.27

>       Fuel                      650.       12.03   {0.750 $/US.gal.}

>       Airframe Maintenance      580.       10.75
>       Engines Maintenance       317.        5.87
>       ________________________________________________

>       Total Ownership          1173.    U.S.$ per trip
>       Total Cash               4225.    U.S.$ per trip
>       Total D.O.C.             5399.    U.S.$ per trip
>       ________________________________________________

>       Utilization             1697      trips/year
>       Block time              1.71      hours
>       Block distance          500.      n.miles
>       Block fuel              5777.     lb.
>       Block fuel/seat         73.       lb./seat
>       D.O.C./ block hour      3157.     U.S.$/hr
>       D.O.C./ seat            68.       U.S.$/seat
>       D.O.C./ seat-n.mile     0.13667   U.S.$/seat-n.mile

>      PAYLOAD-RANGE
>      _____________

>      Range mode: fixed mach, step-up

>      Max.payload / MTOW case
>      _______________________
>      Payload       22016. lb.
>      Range           651. n.miles
>      Fuel          12000. lb.
>      Cruise mach   0.720
>      Cruise alt.   35000. feet

>      Fuel volume limit / MTOW case (kinkpoint)
>      _____________________________
>      Payload       10464. lb.
>      Range          2109. n.miles
>      Fuel          23552. lb.
>      Cruise mach   0.720
>      Cruise alt.   35000. feet

>      Zero payload / TOW=OEW+max.fuel case
>      ____________________________________
>      Payload        zero
>      Range          2351. n.miles
>      TOW           73536. lb.
>      Fuel          23552. lb.
>      Cruise mach   0.720
>      Cruise alt.   35000. feet

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