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Grumman
G-1159 Gulfstream II

The Gulfstream II (G-II) is an American twin engine business jet designed and built by Grumman and then in succession, Grumman American and finally Gulfstream American. Its Grumman model number is G-1159 and its US military designation is C-11 Gulfstream II. It has been succeeded by the Gulfstream III. The first Gulfstream II flew on October 2, 1966.

Grumman: G-1159 Gulfstream III

Role Business jet
National origin United States
Manufacturer Grumman/Gulfstream Aerospace
First flight 2 October 1966
Status In service
Produced 1967–1980
Number built 256
Variants Gulfstream III

 

Grumman

Grumman
G-1159 Gulfstream II

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Grumman
G-1159 Gulfstream II

The Gulfstream II (G-II) is an American twin engine business jet designed and built by Grumman and then in succession, Grumman American and finally Gulfstream American. Its Grumman model number is G-1159 and its US military designation is C-11 Gulfstream II. It has been succeeded by the Gulfstream III. The first Gulfstream II flew on October 2, 1966.

The Gulfstream II is a twin-jet swept wing corporate transport powered by two Rolls-Royce Spey turbofan engines and designed to provide high speed and long range capability without sacrificing the airport performance, reliability, and other operational advantages of its predecessor, the turboprop Gulfstream I. Preliminary design of the wing was influenced by both cruise and low speed considerations. The aft-mounted engine location was selected after extensive analysis and design iterations considering aerodynamic, structural, and ground clearance requirements. 

Design

Airfoil geometry was developed to maximum sweep benefit from the selected planform. The interference problem at the wing-body juncture was treated by modification of the airfoil shape and thickness over the inner third of the wing span. 

The basic airfoils for the main area of the wing are similar to those of the Grumman A-6 Intruder aircraft and utilize NACA 6-series thickness distributions combined with an in-house mean line. A buffet boundary commensurate with the M=.85 speed capability was attained by incorporating a row of co-rotating vortex generators on the outer wing panel. In developing the wing contours, attention was paid to the aircraft’s low speed requirements by tailoring the leading edge radius to preclude leading edge separation. The high lift configuration, consists of a one piece, single-slotted Fowler flap of 30% chord. Stall initiation on the basic wing was found to occur at midspan but spread rapidly to the tip, particularly at large flap deflections. The addition of an upper surface fence at about midspan provided a strong pitch down at the stall, without sacrificing maximum lift, and also afforded an adequate margin between initial and tip stall.

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Grumman G-1159 Gulfstream II (1966)

Grumman had delivered over 150 turboprop Gulfstream Is by the start of 1965 but were gaining competition from the jet powered Lockheed Jetstar, Hawker Siddeley HS.125, Dassault Falcon 20 and the North American Sabreliner. The new generation of business jets didn’t match the range and comfort of the Gulfstream I and customers were demanding a jet powered variant of the Gulfstream I.

When the Rolls-Royce Spey second-generation turbofan became available the program became a reality and a full-scale mock up was created. With 30 firm orders the company launched production go-ahead on 5 May 1965

Specifications

Crew: 2

Capacity: 19 (maximum certified) / 2,900 lb (1,315 kg) 

Length: 79 ft 11 in (24.36 m)

Wingspan: 77 ft 10 in (23.72 m)

Height: 24 ft 6 in (7.47 m)

Empty weight: 39,100 lb (17,735 kg) (basic operating weight)

Gross weight: 65,500 lb (29,710 kg)

Max takeoff weight: 68,200 lb (30,935 kg)

Maximum landing weight: 58,500 lb (26,535 kg)

Powerplant: 2 × Rolls-Royce Spey 511-8 turbofan engines

Stall speed: 105 kn (121 mph, 194 km/h) at MLW, flaps down

Maximum cruising Mach number: M0.85 at max power at 30,000 ft (9,144 m) and AUW of 55,000 lb (24,948 kg)

Never exceed speed: M0.85

Economical cruise speed: M0.77

Range: 3,550 nmi (4,090 mi, 6,570 km) with 8 passengers, NBAA IFR reserves, crew of 3, 2,000 lb (907 kg) / pax

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Seven U.S. Navy squadrons flew the F11F-1: VF-21 and VF-33 in the Atlantic Fleet and VA-156 (redesignated VF-111 in January 1959), VF-24 (redesignated VF-211 in March 1959), VF-51, VF-121, and VF-191 in the Pacific Fleet.

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