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<font color="#000077"> Fokker F70 Sample Analysis </font> </p></h1> <p> </p><hr>
<font color="#000000">
</font><p><font color="#000000">
This sample text output was compiled directly from the Piano model of 
the Fokker F70. Various reports are shown, in no particular order.</font>
</p><blockquote>
<pre>

 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 &amp; 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 &amp; 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 &amp; 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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