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• Boeing 787 -8 (Dreamliner) sample analysis. (2005)

The following results and graphics are derived from the plane file reproduced here which constitutes a complete Piano definition of the Boeing 787-8 using 97 parameters.

Gross design weights conform to values published by Boeing (Sept. 2005), implying significant savings from the use of composites. Adjustments needed in Piano to match these quotes would indicate a challenging task, of the order of -15% on overall structural mass compared to all-metal construction. Historically, weight increases happen regularly during project development. We'll all have to wait and see.

Engine ratings are not yet finalised, and various options may be offered. The generic engine used here has a Boeing equivalent thrust (BET) of 63800 lbf (66540 lbf SLST), and assumes emissions of -30% NOx, -50% HC and +10% CO for a GEnx-64B relative to CF6-80C2B levels. Max climb and cruise ratings are set comparatively high, to provide a good ICA capability. Detailed mission profile calculations can be found at the end of this page.

(Note: The 'airport compatibility' brochure for the Boeing 787 Dreamliner is available here as of June '06).

Update Note - June 2006:
Boeing recently revised the 787 brochure to show a baseline payload of 242 pax over a range of roughly 7860 nm and simultaneously removed their OEW claim. Piano indicates that an increase in OEW to approximately 243500 lb will account for the revised payload-range characteristics (these include Boeing's minor adjustment in fuel capacity). Using a typical value of furnishings-per-pax, the weight increase is largely (but not totally) explained by the extra seating. The data quoted below remain valid at the original OEW (239200 lb, 224 pax configuration). You may choose to reduce all payloads by the difference in OEW depending on an individual airline's delivery specs.

June 21st 2006: More changes have been made to the 787 brochure. Boeing appears ready to revert to generic ZFW-range charts (as opposed to payload-range). This would sidestep the need to claim a specific OEW linked to a specific configuration.

April 2008: The latest assessments of the B787-3, B787-8, B787-9 are now available commercially under Piano-X.

December 2008: B787-8 model released:
The Piano-X model of the Boeing 787-8 has now been released in the public domain and can be downloaded freely, see release note here. It is fully adjustable and supersedes this original sample analysis, which will no longer be updated.

November 2011: B787-8 EIS release:
An updated assessment and Piano-X model reflecting EIS (entry into service) levels of performance are now available here.



3-view of Boeing 787 (click to enlarge)

 GEOMETRY REPORT
 _______________
                                Wing    Stabiliser   Fin 
                                ----    ----------   --- 
 Area, trapezoidal reference   3501.39   832.50    427.50    sq.feet
 Area, piano gross             4028.47   832.50    427.50    sq.feet
 Area, airbus gross            3971.42                       sq.feet
 Area, boeing wimpress         3870.00                       sq.feet
 Area, esdu                    3862.65                       sq.feet
 Area, exposed                 3238.14   636.15    427.50    sq.feet
 Area, wetted                  6591.18   1292.43   868.52    sq.feet

 Aspect Ratio, trapezoidal      10.58      5.00      1.70    
 Aspect Ratio, piano gross       9.20      5.00      1.70   
 Aspect Ratio, airbus gross      9.33
 Aspect Ratio, boeing wimpress   9.58
 Aspect Ratio, esdu              9.59

 Span (excluding winglets)     192.50     64.52     26.96    feet

 Sweepback at 1/4-chord         32.20     36.00     40.00    degrees

 Taper Ratio (trapezoidal)       0.18      0.22      0.33   

 t/c at root                    0.134     0.100     0.100   
 t/c at thickness break         0.094
 t/c at tip                     0.088     0.100     0.100   

 Volume Coefficient (V-bar)               0.921     0.049   
 Mean Aero Chord (trap.wing)    21.12     14.66     17.18    feet
 Arm between MAC 1/4 chords               81.81     77.04    feet

 Wing chord at tip                                5.55       feet
 Wing chord at planform break                    21.06       feet
 Wing chord at root (gross)                      38.94       feet
 Wing chord at c/line (gross)                    45.00       feet
 Wing chord at c/line (notional trapezoidal)     30.83       feet

 Planform break location        0.320  (fraction of exposed semispan)
 Thickness break location       0.333  (fraction of exposed semispan)

 Wing location (station of extended leading edge at c/line):
 55.05 feet    (30.0 % of fuse.length)

 Spar locations (fractions of local trapez.chord):
 Wing root: 0.15, 0.75       Wing tip: 0.15, 0.65

 Fuel capacity  (avail/reqrd = 1.146)
 -------------
 (US.gal.: wing 27008.8, centre 10804.6, tail 0.0, adjust -4873.4)

 Total Available: 32940.00 US.gal. (geometric capacity)
 Total Required : 28749.63 US.gal. (at mtow & design payload)

 Fuselage geometry
 -----------------
 fuselage max. width            18.83    feet
 fuselage max. depth            19.77    feet

 length, total fuselage        183.50    feet
 length, front section          37.00    feet
 length, mid section            81.50    feet
 length, rear section           65.00    feet
 
 wetted area, total fuselage   9480.31   sq.feet
 wetted area, front section    1785.58   sq.feet
 wetted area, mid section      4939.96   sq.feet
 wetted area, rear section     2754.77   sq.feet

 Nacelle geometry
 ----------------
 nacelle length                 18.60    feet
 nacelle max. width             12.00    feet
 nacelle max. depth             12.00    feet
 wetted area per nac.          661.75    sq.feet

 Overall dimensions
 ------------------
 Span over winglets            197.31    feet
 Overall aircraft length       185.56    feet
 Height at top of fin          55.13     feet
 Overall aircraft wetted area  19593.33  sq.feet 



 Boeing 787 -8 (baseline) _______________________
 
 PAYLOAD        224.  PAX = 47040.lb.

 MTOW        476000.  lb.
 OEW         239200.  lb. = 50.3% of mtow

 FUEL-CAP.    32940.  US.gal. Avail/Req=1.15

 SPAN         192.5   feet excl.winglets

 WING-AREA     3501.  sq.feet trapezoidal

 ENG.THRUST   62500.  *2 lbf. reference fn*
              66538.  *2 lbf. available slst

 W/S            136.  p.s.f. trapezoidal

 T/W          0.263   reference
              0.280   available 


Mass barchart - Boeing 787 -8
 Mass Report      (in lb. and % of MTOW)
 ________________________________________

 MTOW   476000.
 OEW    239200.     (50.3%)
 MZFW   340000.     (71.4%)
 MLW    365000.     (76.7%)

 Mass Breakdown            lb.    % MTOW
 ________________________________________
 wing group              60038.   12.61 %
  (struct.box   51372.)
  (flaps         4865.)
  (slats         2398.)
  (spoilers       662.)
  (ailerons       357.)
  (winglets       384.)
 fuselage group          44917.    9.44 %
 stabiliser               5158.    1.08 %
 fin                      2138.    0.45 %
 undercarriage           18605.    3.91 %
 _____________________  _______   _______
 basic structure total  130854.   27.49 %

 dry engines total       22259.    4.68 %
 nacelles total           8603.    1.81 %
 pylons total             4609.    0.97 %
 _____________________  _______   _______
 powerplants total       35471.    7.45 %

 furnishings             41976.    8.82 %
 surface controls         4836.    1.02 %
 fuel systems              917.    0.19 %
 hydraulics               3750.    0.79 %
 electrics                2950.    0.62 %
 avionics                 3003.    0.63 %
 APU                      1276.    0.27 %
 air conditioning         2164.    0.45 %
 misc. systems            8835.    1.86 %
 _____________________  _______   _______
 fixed equipment total   69707.   14.64 %

 manufact. contingency       0.    0.00 %
 _____________________  _______   _______
 Manufact. Empty Mass   236032.   49.59 %  = MEW

 crew                     2205.    0.46 %
 operational items         963.    0.20 %
 _____________________  _______   _______
 Operators Empty Mass   239200.   50.25 %  = OEW

 design payload          47040.    9.88 %
 design fuel            189760.   39.87 %
 _____________________  _______   _______
 Maximum Takeoff Mass   476000.   100   %  = MTOW


 Design Limits
 _____________

 Design cruise point is Mach 0.90 at 37000.feet

 Design dive Mach     MD       0.95
 Design cruise speed  VC       372. KEAS
 Design dive speed    VD       426. KEAS
 Limit    load factor          2.54
 Ultimate load factor          3.81
 Cabin pressure differential   9.18 psi (limit)



Lift / Drag Polar - Boeing 787 -8

 AERODYNAMIC DRAG REPORT at:
 ---------------------------
 MACH                  0.850
 Altitude (pressure)   37000. feet
 KTAS                  487.5
 KEAS                  260.0
 KCAS                  277.9
 Reynolds number       1.873  millions per foot
 Delta-ISA               +0.  deg.C.

 CL                    0.508  based on:
 Reference Area       3870.00 sq.feet  (wimpress)

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

 Cd Zero-Lift              0.01277    (52.4 %)
 Cd Lift-Induced           0.01022    (41.9 %)
 Cd Compressibility        0.00071    ( 2.9 %)
 Cd Trim                   0.00069    ( 2.8 %)
 Delta Cd (polar-mod)      0.00000    ( 0.0 %)
                           -------    --------
 Cd Total                  0.02439    ( 100 %)

 Aerodynamic Boundaries:
 -----------------------
 Divergence Mach         0.864 {at the given CL 0.508}
 Initial Buffet Mach     0.875 {at the given CL 0.508}
 Initial Buffet CL       0.624 {at the given Mach 0.850}

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

 Wing                   18.313  sq.feet    (37.0 %)
 Winglets                0.143  sq.feet    ( 0.3 %)
 Fuselage & fairing     19.367  sq.feet    (39.2 %)
 Stabiliser              4.049  sq.feet    ( 8.2 %)
 Fin                     2.975  sq.feet    ( 6.0 %)  
 Nacelles (total)        4.591  sq.feet    ( 9.3 %)
 User CdS Increment      0.000  sq.feet    ( 0.0 %)
                       -------             --------
 Total Cd0*S            49.438  sq.feet    ( 100 %)

 Overall Lift / Drag Ratio = 20.84 
 =================================

 Total Lift Force      450002. lbf.
 Total Drag Force       21598. lbf. (10799.lbf. per engine) 


 Engine / Airframe Performance:
 ------------------------------
 Total Fuel Flow at Thrust=Drag:       11402. lb/hr
 Specific Fuel Consumption (SFC)       0.5279 lb/hr/lbf
 Specific Air Range (SAR)              0.0428 nm/lb
 Emissions Index, NOx                  11.88  g/kg.
 Available Total Thrust at MCR:        25521. lbf.
 Available Total Thrust at MCL:        27449. lbf.

 Instantaneous Performance Reserves at Weight=Lift:
 
 RoC at MCR, constant Mach 0.850:      429. feet/min
 RoC at MCR, constant 278.KCAS:        300. feet/min

 RoC at MCL, constant Mach 0.850:      640. feet/min
 RoC at MCL, constant 278.KCAS:        447. feet/min



  Drag Tabulation @ 37000.feet, Ref.Area 3870.00 sq.feet (wimpress)
  ------------------------------------------------------------------------------

  Mach   CL      Cd{0}     Cd{lift}  Cd{comp}  Cd{trim}  Cd{mod}   Cd{tot}   L/D

  0.800  0.400   0.01299   0.00645   0.00002   0.00065   +0.00000  0.02011   19.90
  0.800  0.450   0.01299   0.00812   0.00002   0.00068   +0.00000  0.02179   20.65
  0.800  0.500   0.01299   0.00997   0.00002   0.00069   +0.00000  0.02366   21.13
  0.800  0.550   0.01299   0.01200   0.00002   0.00071   +0.00000  0.02571   21.39
  0.800  0.600   0.01299   0.01421   0.00005   0.00071   +0.00000  0.02796   21.46
  0.800  0.650   0.01299   0.01660   0.00008   0.00071   +0.00000  0.03038   21.40

  0.820  0.400   0.01291   0.00643   0.00004   0.00065   +0.00000  0.02003   19.97
  0.820  0.450   0.01291   0.00810   0.00007   0.00067   +0.00000  0.02175   20.69
  0.820  0.500   0.01291   0.00994   0.00010   0.00069   +0.00000  0.02364   21.15
  0.820  0.550   0.01291   0.01197   0.00014   0.00070   +0.00000  0.02572   21.38
  0.820  0.600   0.01291   0.01418   0.00020   0.00071   +0.00000  0.02800   21.43
  0.820  0.650   0.01291   0.01657   0.00029   0.00071   +0.00000  0.03048   21.33

  0.850  0.400   0.01279   0.00640   0.00029   0.00065   +0.00000  0.02013   19.87
  0.850  0.450   0.01279   0.00806   0.00042   0.00067   +0.00000  0.02194   20.51
  0.850  0.500   0.01279   0.00990   0.00065   0.00069   +0.00000  0.02404   20.80
  0.850  0.550   0.01279   0.01192   0.00104   0.00070   +0.00000  0.02646   20.78
  0.850  0.600   0.01279   0.01413   0.00167   0.00071   +0.00000  0.02930   20.48
  0.850  0.650   0.01279   0.01651   0.00264   0.00071   +0.00000  0.03264   19.91

  0.870  0.400   0.01272   0.00636   0.00111   0.00064   +0.00000  0.02083   19.20
  0.870  0.450   0.01272   0.00801   0.00174   0.00067   +0.00000  0.02313   19.45
  0.870  0.500   0.01272   0.00985   0.00270   0.00069   +0.00000  0.02595   19.27
  0.870  0.550   0.01272   0.01187   0.00413   0.00070   +0.00000  0.02941   18.70
  0.870  0.600   0.01272   0.01406   0.00617   0.00070   +0.00000  0.03365   17.83
  0.870  0.650   0.01272   0.01644   0.00901   0.00070   +0.00000  0.03887   16.72



Payload-Range Altitude Capability SFC loop, L/D

  Calculating design range...done.

  RANGE REPORT  {design}
  ____________

  {TOW 476000.lb./ OEW 239200.lb./ Fuel 189760.lb./ Payload 47040.lb.}

  Range mode: fixed mach, step-up cruise 

  Climb schedule: 250./ 277.kcas/ mach 0.825 above 35738.feet

  Cruise at Mach = 0.850  {FL 370 410}

  ICA 37000.feet, 488.ktas, 278.kcas, CL=0.53, 11186.lbf./eng=MCR-12%
  FCA 41000.feet, 488.ktas, 253.kcas, CL=0.42, 7690.lbf./eng=MCR-26%

                Distance        Time      Fuelburn
                (n.miles)      (min.)      (lb.)
                _________      ______     _______
  Climb            181.          28.        9529.   {S.L to ICA}
  Cruise          8034.         989.      161751.   {ICA to ICA}
  Descent          129.          22.         476.   {ICA to S.L}
                _________      ______     _______
  Trip  total     8345.        1039.      171756.
  Block total   =========      1057.      174613.

  Emissions: taxi,t/o  climb   cruise  descent  app,taxi   total
  (lb.NOx)     30.2    148.3   1798.2      1.1      2.6   1980.4
  (lb.HC)      0.16     0.56    19.20     0.69     0.26    20.87
  (lb.CO)       4.8      7.0    481.3     16.8      6.6    516.4

  Manoeuvre allowances:
  taxi-out    2000. lb. {extra to t/o mass}    10.0 min.
  takeoff      458. lb.                         1.0 min.
  approach     263. lb.                         2.0 min.
  taxi-in      137. lb. {taken from reserves}   5.0 min.

  Reserves {at landing mass 303524.lb.}:

  Diversion distance          200. n.miles
  Diversion mach            0.535
  Diversion altitude        22117. feet
  Diversion fuel             5040. lb.

  Holding time                 30. minutes
  Holding mach              0.276
  Holding altitude           5000. feet
  Holding fuel               3620. lb.

  Contingency fuel           8624. lb. {5.% of mission fuel}

  Total Reserve fuel        17284. lb.


Specific Air Range charts (NAMS) at FL:

FL310 FL330 FL350
FL370 FL390 FL410


Here is the Complete Cruise Performance Tabulation (large text document)



 TAKEOFF PERFORMANCE {476000.lb., altitude 0.feet, ISA+15.deg.C.}
 ___________________

 JAR25 Takeoff Field Length     9255. feet 

 115% Factored All-Eng.Dist.    8785. feet
 Balanced Field Length          9255. feet

 2nd Segment Climb Gradient     3.49 %

 Takeoff CLmax            1.91  {wimpress ref.area}
 Takeoff Vstall           138.  keas
 Takeoff Vmc              132.  keas
 Takeoff Vfail            157.  keas
 Takeoff V2               165.  keas
 L/D at 2nd segment      14.15  {incl.windmill & asymm.}

 Takeoff Wing Loading     136.  p.s.f.{trap.W/S}
 Takeoff Thrust/Weight   0.280  available static 


 LANDING PERFORMANCE {365000.lb., altitude 0.feet, ISA+0.deg.C.}
 ___________________

 JAR25 Landing Field Length     4986. feet

 Landing Distance (LFL*0.6)     2992. feet
 Landing Ground Roll            2037. feet

 Landing  CLmax           2.66  {wimpress ref.area}
 Landing  Vstall          102.  keas
 Approach Speed           133.  keas
 Approach L/D             6.96  {gear down}



Takeoff performance

WAT limits

Landing performance

Lowspeed L/D polar

Balanced Field Length



Block Fuel vs Range

Here is the Block Missions Performance Table (large text document)


Design Mission Profile

Here is the Detailed Design Mission (large text document)


This is an independent analysis of the Boeing 787 -8 based on preliminary information.
Copyright © 2006 Lissys Ltd

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