3-view of Boeing 787 (click to enlarge)
GEOMETRY REPORT
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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 -8Mass 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