Search filter

    • Year
      1906
      2018
    • Length
      19 m
      30 m
    • Height
      5 m
      9 m
    • Width
      1 m
      8 m
    • Diameter
      3 m
      9 m
    • Wing area
      60 m2
      91 m2
    • Wingspan (Beam)
      16 m
      26 m
    • Wing loading
      3 kg/m2
      829 kg/m2
    • Swept
      4 m
      10 m
    • Sweep
      25 deg
      68 deg
    • Aspect ratio
      1
      26
    • Disc area
      1 m2
      460 m2
    • Main rotor diameter
      1 m
      62 m
    • Rotor number
      1 qt
      8 qt
    • Blades per rotor
      4 qt
      5 qt
    • Disc loading
      17 kg/m2
      73 kg/m2
    • Tail rotor diameter
      0 m
      5 m
    • Empty weight
      13260 kg
      19892 kg
    • Max. takeoff weight (Gross weight)
      23768 kg
      35652 kg
    • Loaded weight
      23768 kg
      35654 kg
    • Crew
      1 per.
      3 per.
    • Useful load
      26 kg
      90700 kg
    • Payload
      23 kg
      122470 kg
    • Capacity passengers
      15 per.
      23 per.
    • Hardpoints
      1 qt
      2576 qt
    • Ground Speed
      96 km/h
      1500 km/h
    • Max. Speed
      748 km/h
      1124 km/h
    • Сruise Speed
      622 km/h
      934 km/h
    • Stall Speed
      40 km/h
      258 km/h
    • Landing Speed
      68 km/h
      270 km/h
    • Minimum control speed
      24 km/h
      113 km/h
    • Never exceed speed
      107 km/h
      1050 km/h
    • Fuel Capacity
      23 l
      320000 l
    • Fuel External
      142 l
      10025 l
    • Power/mass
      0 hp/kg
      23 hp/kg
    • Thrust/weight
      0 kN/kg
      3 kN/kg
    • Afterburning thrust
      29 kN/kg
      980 kN/kg
    • Total Power
      0 hp
      60000 hp
    • Thrust
      81 kN
      123 kN
    • Service ceiling
      10972 m
      16458 m
    • Static ceiling
      3 m
      5485 m
    • Range (Ferry range)
      5308 km
      7962 km
    • Range PTB (Ferry range)
      720 km
      10000 km
    • Сombat radius
      277 km
      7210 km
    • Endurance
      0 h
      150 h
    • Takeoff roll
      20 m
      3200 m
    • Landing roll
      20 m
      2570 m
    • Maximum glide ratio
      7
      43
    • Load factor from
      2 G
      9 G
    • Rate of climb
      1 m/min
      36000 m/min
    • Rate of sink
      36 m/min
      56 m/min
    • Time to altitude
      0 min
      105 min
    • Propellers
      1 qt
      8 qt
    • Prop diameter
      1 m
      6 m
    • Prop blade number
      1 qt
      8 qt
    • Guns
      1 qt
      18 qt
    • Bombs
      1 qt
      250 qt
    • Missiles
      1 qt
      24 qt
    • Rockets
      1 qt
      76 qt
    • Torpedoes
      1 qt
      4 qt
    • Bombs weight
      2 kg
      39000 kg
    • Rockets weight
      1 kg
      48 kg
    • Number built
      206 qt
      310 qt
    • Price
      41 USD
      750000000 USD

Grumman Gulfstream II

TypeAircraft
Company

Grumman Aerospace Corporation

Gulfstream Aerospace Corporation

Scheme

Monoplane

Low wing

Geometry
Length (m)
1.9
 
24.4
88.7
Height (m)
0.6
 
7.5
50.1
Wings
Wing area (m2)
1.1
 
75.2
925
Wingspan (Beam) (m)
0.1
 
21.0
95
Weights
Empty weight (kg)
8
 
16,576
276,800
Max. takeoff weight (Gross weight) (kg)
154
 
29,710
575,000
Loaded weight (kg)
5
 
29,711
242,500
Capacity
Crew (per.)
1
 
2
112
Capacity passengers (per.)
1
 
19
400
maximum certified
Speeds
Max. Speed (km/h)
25
 
936
28,165
Сruise Speed (km/h)
52
 
778
3,087
Power
Thrust (kN)
1.5
 
102
1,914
2 powerplants 51 kN each
Performance
Service ceiling (m)
0.6
 
13,715
161,544
Range (Ferry range) (km)
4
 
6,635
40,700
Stat
Number built (qt)
0
 
258
43,000
Introduction 1966
First flight 02.10.1966
The 60th were the time when business aircraft were growing in popularity. This fact, as well as relative success of Grumman Gulfstream I, made the company start the development of the second generation of bizjets.

Preliminary talks with potential customers, most of whom already had Gulfstream I in service, elicited the necessity in fast aircraft with transoceanic range of flight and big and comfortable cabin. Also they wanted a plane with good flight characteristics and capability to work with short runaways. All these features were incorporated in new Gulfstream model that initially had a name G. 1159.

The manufacturer decided to use 2 Rolls-Royce Spey RB.168 Mk 511-8 turbofan engines of 51 kN thrust each. Considering aerodynamic basics, structural and clearance requirements it was decided to mount the engines in the aft of the plane. The modifications were made also with empennage.
By the time when the company finished the a full-scale mock-up of Gulfstream II it had already received 30 firm orders that resulted in programme speed-up. This why there were no prototype as such, and the first plane produced conducted its maiden flight on October 2, 1966.

During test period that was revealed that the aircraft stall characteristics are satisfactory but did not exclude stall penetration to the point of secondary stall pitchup. However Grumman decided to refuse from long test research in order to achieve perfect stall characteristics instead they limit stall penetration with mechanical means which are stick shaker and stick pusher. In October 1967 Gulfstream II received its FAA certifications and was delivered to the customer (National Distillers and Chemical Corporation of New York) in December of the same year. Before the first delivery Gulfstream II was sent over Atlantic for completion. Thanks to that flight this aircraft became the first to fly non-stop over Atlantic in both directions.

The manufacturing and modifications of the plane continued till 1975. During this time Grumman built a plant in Savannah, Georgia; and 40th Gulfstream II became the last produced in Bethpage, New York. In December 1967 the Savannah plant started production. Furthermore in 1973 Grumman created corporation “Grumman American Aviation” and in 1978 it was renamed “Gulfstream American”.

During years of production several variants were produced.

The original Gulfstream II received certification in 1967 and could accommodate 14 passengers it was very requested by charter operators and private individuals.

There was also series of aircraft with tip tanks that ware called Gulfstream II TT, the model was certified in 1977.

In September 1981 the Gulfstream IIB variant was certified. Two years after the production of original Gulfstream II had stopped. It differed from the original aircraft by winglets wings of Gulfstream III. This modification was proposed to all Gulfstream II owners in order to increase range and decrease expenses on the airplane maintenance.

The airplane was in wide use by operators and private customers. Also it was widely operated by different Army forces for VIP transportations and cargo transportation. But even now some airplanes are used for special missions. Several are used by NASA mostly as Shuttle Training Aircraft.
One more modification Gulfstream IISP saw the world in the beginning of 90 when it completely substituted Gulfstream II on the production line. With this variant designers could improve flight characteristics without sacrificing weight characteristic of the plane.

In total there were 258 aircraft built. In 2013 the FAA changed some rules so that old variants of Gulfstream II weren’t allowed flying if they had not been modified before. Gulfstream II was one of the most popular aircraft of Grumman and it definitely carved out a niche on the market of business jets.

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Comments

  • Maxim Anohin Jan. 5, 2016, 12:32 p.m.

    Nice airplane!