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• Gulfstream G550 (GV-SP) sample analysis.

Detailed description of the Gulfstream 550 (best fit to 2003 specification). All of the following results and graphics were derived by Piano from the plane file reproduced here which constitutes a complete Piano definition of the G550 using around 90 parameters. Integrated mission outputs (including environmental emissions) appear near the end of this page.

(The manufacturer's basic specification of the Gulfstream 550 is available here).

(Last revised Feb. 2006, minor definition mods to basic file, performance & missions reworked.)

April 2008: An assessment of the Gulfstream G650 is now available under Piano-X.


Gulfstream G550 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
 ------------------
 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)
  ------------------------------------------------------------------------------

  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)


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