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The Gulfstream II (G-II) is an American twin engine business jet designed and first built by Grumman, then Grumman American and finally Gulfstream American. It was 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. Airfoil geometry was developed to maximum sweep benefit from the selected planform.

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.

Grumman Aerospace Corporation,

Grumman Aerospace Corporation
Grumman Gulfstream II (G-II)

General characteristics

Crew: 2
Capacity: 19 (maximum certified) / 2,900 lb (1,315 kg) maximum payload
Length: 79 ft 11 in (24.36 m)
Wingspan: 77 ft 10 in (23.72 m)
Height: 24 ft 6 in (7.47 m)
Wing area: 934.6 sq ft (86.83 m²)
Airfoil: stn.50: NACA 0012 modified; stn 145: NACA 63A-009.5; stn 385: NACA 64 series modified

Powerplant

Empty weight: 39,100 lb (17,735 kg) (basic operating weight)
Maximum zero-fuel weight: 42,000 lb (19,051 kg)
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)
Fuel capacity: 28,300 lb (12,837 kg) maximum
Powerplant: 2 × Rolls-Royce Spey 511-8 turbofan engines, 11,400 lbf (51 kN) thrust each

Specifications

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

3,970 nmi (4,569 mi; 7,352 km) with NBAA VFR reserves

Service ceiling: 45,000 ft (14,000 m)
Rate of climb: 3,800 ft/min (19 m/s)

1,200 ft/min (6.10 m/s) on one engine

Related development

Special Links Grumman Aerospace Corporation, Grumman Gulfstream II (G-II)

Links to Youtube & Others

Production of the Gulfstream II ended at Savannah in December 1979.[6] Between 1981 and 1987 43 aircraft were converted to Gulfstream IIB standard with new wings and advanced avionics based on the newer Gulfstream III.

Grumman Gulfstream II (G-II)

The F-14 Tomcat was designed as both an air superiority fighter and a long-range naval interceptor.

Youtube Link

At the time of filming, the only recognizable star in the movie was Tom Cruise, who was known as a teen idol from 1983’s “Risky Business.”.

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Grumman Gulfstream II (G-II)

Grumman Aerospace Gulfstream II (G-II)

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History Grumman Aerospace
Gulfstream II (G-II)

The Gulfstream II (G-II) is an American twin engine business jet designed and first built by Grumman, then Grumman American and finally Gulfstream American. It was succeeded by the Gulfstream III. The first Gulfstream II flew on October 2, 1966

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Grumman Gulfstream II (G-II)