Gulfstream G550 3-view (click to enlarge)
GEOMETRY REPORT
_______________
Wing Stabiliser Fin (excl.dorsal)
---- ---------- ---
Area, trapezoidal reference 1137.00 244.87 140.16 sq.feet
Area, piano gross 1141.15 244.87 140.16 sq.feet
Area, airbus gross 1132.11 sq.feet
Area, boeing wimpress 1137.00 sq.feet
Area, esdu 1137.00 sq.feet
Area, exposed 987.38 244.87 140.16 sq.feet
Area, wetted 2004.28 496.34 284.43 sq.feet
Aspect Ratio, trapezoidal 7.36 5.05 0.98
Aspect Ratio, piano gross 7.34 5.05 0.98
Aspect Ratio, airbus gross 7.39
Aspect Ratio, boeing wimpress 7.36
Aspect Ratio, esdu 7.36
Span (excluding winglets) 91.50 35.16 11.72 feet
Sweepback at 1/4-chord 27.00 30.00 37.00 degrees
Taper Ratio (trapezoidal) 0.26 0.41 0.65
t/c at root 0.100 0.090 0.095
t/c at thickness break n/a
t/c at tip 0.083 0.090 0.095
Volume Coefficient (V-bar) 0.612 0.041
Mean Aerodynamic Chord 13.86 7.37 12.14 feet
Arm between MAC 1/4 chords 39.36 30.26 feet
Wing chord at tip 5.13 feet
Wing chord at planform break n/a feet
Wing chord at root (gross) 18.48 feet
Wing chord at c/line (gross) 20.78 feet
Wing chord at c/line (notional trapezoidal) 19.72 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):
33.90 feet (39.5 % of fuse.length)
Spar locations (fractions of local trapez.chord):
Wing root: 0.08, 0.7 Wing tip: 0.14, 0.67
Fuel capacity (avail/reqrd = 0.995)
-------------
(US.gal.: wing 4783.1, centre 1071.4, tail 0.0, adjust 309.5)
Total Available: 6164.00 US.gal. (geometric capacity)
Total Required : 6194.03 US.gal. (at mtow & design payload)
** WARNING: Fuel capacity shortfall is 30.03 US.gal. **
Fuselage geometry
-----------------
fuselage max. width 7.83 feet
fuselage max. depth 7.83 feet
length, total fuselage 85.83 feet
length, front section 14.61 feet
length, mid section 38.47 feet
length, rear section 32.74 feet
wetted area, total fuselage 1731.70 sq.feet
wetted area, front section 256.29 sq.feet
wetted area, mid section 945.99 sq.feet
wetted area, rear section 529.42 sq.feet
Nacelle geometry
----------------
nacelle length 16.24 feet
nacelle max. width 5.91 feet
nacelle max. depth 5.91 feet
wetted area per nac. 260.53 sq.feet
Overall dimensions
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Span over winglets 93.50 feet
Overall aircraft length 96.38 feet
Height at top of fin 22.72 feet
Overall aircraft wetted area 5096.18 sq.feet
Gulfstream G550 ______________________________
PAYLOAD 8. PAX = 1600.lb.
MTOW 91000. lb.
OEW 48300. lb. = 53.1% of mtow
FUEL-CAP. 6164. US.gal. Avail/Req=1.00
SPAN 91.5 feet excl.winglets
WING-AREA 1137. sq.feet trapezoidal
ENG.THRUST 16000. *2 lbf. reference fn*
15385. *2 lbf. available slst
W/S 80. p.s.f. trapezoidal
T/W 0.352 reference
0.338 available
Mass barchart
Mass Report (in lb. and % of MTOW) ________________________________________ MTOW 91000. OEW 48300. (53.1%) MZFW 54500. (59.9%) MLW 75300. (82.7%) Mass Breakdown lb. % MTOW ________________________________________ wing group 10810. 11.88 % (struct.box 8401.) (flaps 1681.) (spoilers 222.) (ailerons 165.) (winglets 339.) fuselage group 7381. 8.11 % stabiliser 1402. 1.54 % fin (incl.dorsal) 823. 0.90 % undercarriage 3113. 3.42 % _____________________ _______ _______ basic structure total 23529. 25.86 % dry engines total 6307. 6.93 % nacelles total 3141. 3.45 % pylons total 756. 0.83 % _____________________ _______ _______ powerplants total 10204. 11.21 % furnishings 4800. 5.27 % surface controls 1294. 1.42 % fuel systems 628. 0.69 % hydraulics 683. 0.75 % electrics 1233. 1.35 % avionics 701. 0.77 % APU 84. 0.09 % air conditioning 77. 0.08 % misc. systems 2275. 2.50 % _____________________ _______ _______ fixed equipment total 11775. 12.94 % manufact. contingency 0. 0.00 % _____________________ _______ _______ Manufact. Empty Mass 45508. 50.01 % = MEW crew 882. 0.97 % operational items 1910. 2.10 % _____________________ _______ _______ Operators Empty Mass 48300. 53.08 % = OEW design payload 1600. 1.76 % design fuel 41100. 45.16 % _____________________ _______ _______ Maximum Takeoff Mass 91000. 100 % = MTOW Design Limits _____________ Design cruise point is Mach 0.85 at 39000.feet Design dive Mach MD 0.90 Design cruise speed VC 355. KEAS Design dive speed VD 410. KEAS Limit load factor 3.28 Ultimate load factor 4.92 Cabin pressure differential 10.17 psi (limit) NOTE: Design TOW & range limited by fuel capacity.
Lift/Drag polar
AERODYNAMIC DRAG REPORT at:
---------------------------
MACH 0.800
Altitude (pressure) 45000. feet
KTAS 458.9
KEAS 201.9
KCAS 215.5
Reynolds number 1.200 millions per foot
Delta-ISA +0. deg.C.
CL 0.510 based on:
Reference Area 1137.00 sq.feet (trapezoidal)
Drag Coefficients based on ref.area
-----------------------------------
Cd Zero-Lift 0.01519 (54.8 %)
Cd Lift-Induced 0.01151 (41.5 %)
Cd Compressibility 0.00078 ( 2.8 %)
Cd Trim 0.00024 ( 0.9 %)
Delta Cd (polar-mod) 0.00000 ( 0.0 %)
------- --------
Cd Total 0.02771 ( 100 %)
Aerodynamic Boundaries:
-----------------------
Divergence Mach 0.788 {at the given CL 0.510}
Initial Buffet Mach 0.865 {at the given CL 0.510}
Initial Buffet CL 0.740 {at the given Mach 0.800}
Zero-Lift Component Breakdown (Drag Areas,= Cd*S = D/q)
-----------------------------
Wing 6.025 sq.feet (34.9 %)
Winglets 0.194 sq.feet ( 1.1 %)
Fuselage & fairing 4.974 sq.feet (28.8 %)
Stabiliser 2.290 sq.feet (13.3 %)
Fin 1.206 sq.feet ( 7.0 %) (incl.dorsal)
Nacelles (total) 2.578 sq.feet (14.9 %)
User CdS Increment 0.000 sq.feet ( 0.0 %)
------- --------
Total Cd0*S 17.266 sq.feet ( 100 %)
Overall Lift / Drag Ratio = 18.40
=================================
Total Lift Force 80000. lbf.
Total Drag Force 4348. lbf. (2174.lbf. per engine)
Engine / Airframe Performance:
------------------------------
Total Fuel Flow at Thrust=Drag: 2788. lb/hr
Specific Fuel Consumption (SFC) 0.6414 lb/hr/lbf
Specific Air Range (SAR) 0.1646 nm/lb
Emissions Index, NOx 8.19 g/kg.
Available Total Thrust at MCR: 4541. lbf.
Available Total Thrust at MCL: 4963. lbf.
Instantaneous Performance Reserves at Weight=Lift:
RoC at MCR, constant Mach 0.800: 112. feet/min
RoC at MCR, constant 216.KCAS: 80. feet/min
RoC at MCL, constant Mach 0.800: 357. feet/min
RoC at MCL, constant 216.KCAS: 257. feet/min
Drag Tabulation @ 45000.feet, Ref.Area 1137.00 sq.feet (trapezoidal)
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Mach CL Cd{0} Cd{lift} Cd{comp} Cd{trim} Cd{mod} Cd{tot} L/D
0.800 0.400 0.01519 0.00716 0.00049 0.00030 +0.00000 0.02315 17.28
0.800 0.450 0.01519 0.00902 0.00059 0.00028 +0.00000 0.02508 17.95
0.800 0.500 0.01519 0.01108 0.00074 0.00025 +0.00000 0.02725 18.35
0.800 0.550 0.01519 0.01333 0.00103 0.00020 +0.00000 0.02976 18.48
0.800 0.600 0.01519 0.01579 0.00165 0.00015 +0.00000 0.03278 18.30
0.800 0.650 0.01519 0.01843 0.00313 0.00009 +0.00000 0.03684 17.64
0.820 0.400 0.01510 0.00716 0.00112 0.00030 +0.00000 0.02368 16.89
0.820 0.450 0.01510 0.00902 0.00131 0.00028 +0.00000 0.02571 17.50
0.820 0.500 0.01510 0.01108 0.00172 0.00025 +0.00000 0.02814 17.77
0.820 0.550 0.01510 0.01333 0.00250 0.00020 +0.00000 0.03113 17.67
0.820 0.600 0.01510 0.01579 0.00403 0.00015 +0.00000 0.03507 17.11
0.820 0.650 0.01510 0.01843 0.00724 0.00009 +0.00000 0.04085 15.91
0.850 0.400 0.01496 0.00716 0.00335 0.00030 +0.00000 0.02577 15.52
0.850 0.450 0.01496 0.00902 0.00421 0.00028 +0.00000 0.02846 15.81
0.850 0.500 0.01496 0.01108 0.00578 0.00025 +0.00000 0.03206 15.59
0.850 0.550 0.01496 0.01333 0.00840 0.00020 +0.00000 0.03689 14.91
0.850 0.600 0.01496 0.01579 0.01286 0.00015 +0.00000 0.04376 13.71
0.850 0.650 0.01496 0.01843 0.02101 0.00009 +0.00000 0.05448 11.93
0.870 0.400 0.01487 0.00716 0.00677 0.00030 +0.00000 0.02910 13.75
0.870 0.450 0.01487 0.00902 0.00869 0.00028 +0.00000 0.03286 13.70
0.870 0.500 0.01487 0.01108 0.01193 0.00025 +0.00000 0.03812 13.12
0.870 0.550 0.01487 0.01333 0.01690 0.00020 +0.00000 0.04530 12.14
0.870 0.600 0.01487 0.01579 1.00000 0.00015 +0.00000 1.03080 0.58
0.870 0.650 0.01487 0.01843 1.00000 0.00009 +0.00000 1.03339 0.63
 Payload-Range |
 Altitude Capability |
 Climb Time |
Calculating design range...done.
RANGE REPORT {design}
____________
{TOW 90799.lb./ OEW 48300.lb./ Fuel 40899.lb./ Payload 1600.lb.}
Range mode: fixed mach, step-up cruise
Climb schedule: 250./ 277.kcas/ mach 0.797 above 34040.feet
Cruise at Mach = 0.800 {FL 410 450 490 510}
ICA 41000.feet, 459.ktas, 237.kcas, CL=0.46, 2400.lbf./eng=MCR-14%
FCA 51000.feet, 459.ktas, 187.kcas, CL=0.45, 1519.lbf./eng=MCR-10%
Distance Time Fuelburn
(n.miles) (min.) (lb.)
_________ ______ _______
Climb 144. 22. 2373. {S.L to ICA}
Cruise 6504. 850. 35085. {ICA to ICA}
Descent 101. 17. 230. {ICA to S.L}
_________ ______ _______
Trip total 6748. 889. 37687.
Block total ========= 908. 38486.
Emissions: taxi,t/o climb cruise descent app,taxi total
(lb.NOx) 4.9 34.3 269.5 0.9 1.5 311.0
(lb.HC) 0.23 0.07 3.36 0.38 0.13 4.18
(lb.CO) 6.7 4.0 260.0 9.5 3.8 284.1
Manoeuvre allowances:
taxi-out 400. lb. {extra to t/o mass} 10.0 min.
takeoff 159. lb. 1.0 min.
approach 138. lb. 2.5 min.
taxi-in 102. lb. {taken from reserves} 5.0 min.
Reserves {at landing mass 52814.lb.}:
Diversion distance 200. n.miles
Diversion mach 0.548
Diversion altitude 30959. feet
Diversion fuel 1578. lb.
Holding time 30. minutes
Holding mach 0.217
Holding altitude 5000. feet
Holding fuel 1336. lb.
Contingency fuel 0. lb. {0.% of mission fuel}
Total Reserve fuel 2914. lb.
Specific Air Range charts (NAMS) at FL:
 FL410 |
 FL430 |
 FL450 |
 FL470 |
 FL490 |
 FL510 |
Here is the Complete Cruise Performance Tabulation (large text document)
TAKEOFF PERFORMANCE {91000.lb., altitude 0.feet, ISA+0.deg.C.}
___________________
JAR25 Takeoff Field Length 5934. feet
115% Factored All-Eng.Dist. 5695. feet
Balanced Field Length 5934. feet
2nd Segment Climb Gradient 5.82 %
Takeoff CLmax 1.53 {trapezoidal ref.area}
Takeoff Vstall 124. keas
Takeoff Vmc 86. keas
Takeoff Vfail 142. keas
Takeoff V2 149. keas
L/D at 2nd segment 12.87 {incl.windmill & asymm.}
Takeoff Wing Loading 80. p.s.f.{trap.W/S}
Takeoff Thrust/Weight 0.338 available static
LANDING PERFORMANCE {75300.lb., altitude 0.feet, ISA+0.deg.C.}
___________________
JAR25 Landing Field Length 4612. feet
Landing Distance (LFL*0.6) 2767. feet
Landing Ground Roll 1435. feet
Landing CLmax 1.99 {trapezoidal ref.area}
Landing Vstall 99. keas
Approach Speed 129. keas
Approach L/D 6.34 {gear down}
 Takeoff performance |
 WAT limits |
 Lowspeed L/D polar |
 Balanced Field Length |
Block Fuel vs Range
Here is the Block Missions Performance Table (large text document)
Design Mission Profile @ M.80, step-up cruise
Here is the detailed Design Mission at Mach 0.80 (large text document)
Sample Mission Profile @ M.85, drift-up
Here is a sample Mission at Mach 0.85 (large text document)
Sample Mission Profile @ M.87, step-up
Here is a sample Mission at Mach 0.87 (large text document)