Gulfstream Aerospace G-IV-SP Gulfstream IV Aircraft Data
The Gulfstream IV (or G-IV or GIV) and derivatives are a family of twinjet aircraft, mainly for private or business use. They were designed and built by Gulfstream Aerospace, a General Dynamics company based in Savannah, Georgia, United States, from 1985 until 2018. Aircraft power is provided by two Rolls-Royce RB.183 Tay turbofans. Upon delivery of the last G450, over 900 GIV/GIV-SP/G450 units had been produced. The last G450 was delivered on 19 January 2018 after 365 deliveries over 12 years, ending a 30-year production run, to be replaced by the G500.
Gulfstream, in collaboration with Grumman, began work on the Gulfstream IV in March 1983 as a re-engined, stretched fuselage derivative of the Gulfstream III. A decision to redesign the wing structure for weight reduction presented an opportunity for an aerodynamic redesign of the wing to reduce cruise drag and increase range. Wing contour modifications had to be restricted to the forward 65% of wing chord so that no redesign of the control surfaces would be necessary. Modification of the inboard wing would have entailed a redesign of the fuselage floor structure, consequently this region of the wing was not modified. Outboard wing modifications were aimed at reducing the peak sub-critical pressure coefficient and moving it aft in an effort to reduce shock strength and increase shock sweep. The Gulfstream IV wing has a weaker, more swept outboard shock resulting in a lower cruise drag. Other benefits arising from this design are a lower root bending moment due to the more inboard center of pressure, a lower stall speed due to washout and a larger fuel volume due to increased chord. These aerodynamic improvements result in an increase in range of over 300 nautical miles.
Gulfstream, in collaboration with Grumman, began work on the Gulfstream IV in March 1983 as a re-engined, stretched fuselage derivative of the Gulfstream III. A decision to redesign the wing structure for weight reduction presented an opportunity for an aerodynamic redesign of the wing to reduce cruise drag and increase range. Wing contour modifications had to be restricted to the forward 65% of wing chord so that no redesign of the control surfaces would be necessary. Modification of the inboard wing would have entailed a redesign of the fuselage floor structure, consequently this region of the wing was not modified. Outboard wing modifications were aimed at reducing the peak sub-critical pressure coefficient and moving it aft in an effort to reduce shock strength and increase shock sweep. The Gulfstream IV wing has a weaker, more swept outboard shock resulting in a lower cruise drag. Other benefits arising from this design are a lower root bending moment due to the more inboard center of pressure, a lower stall speed due to washout and a larger fuel volume due to increased chord. These aerodynamic improvements result in an increase in range of over 300 nautical miles.
- Country of Origin:
- First Flight: September 19, 1985
- Initial Service Date:
- No. Built: 900
- No. In Service: 900 (approx.)
- No. of Hardpoints: 0
- Crew: 2
Power:
Rolls-Royce Tay 611-8 at 13,850 lbf
Weapons:
N/A
Dimensions:
Length: | 88 feet 4 in. |
Wing Span: | 77 feet 10 in. |
Wing Area: | 950.39 sq.ft |
Height: | 24 feet 5 in. |
Empty Weight: | 35,500 lbs |
Max. Weight: | 74,600 lbs |
Performance:
Max. Speed: | 581 mph |
Cruise Speed: | 561 mph |
Service Ceiling: | 45,000 ft. |
Normal Range: | 4,220 nm |
Max. Range: | 4,220 nm |
Operators:
Botswana Air ForceSultan Of Brunei (Government)
Chilean Air Force
Côte d'Ivoire Air Force as a VIP transport (Ivory Coast)
Egyptian Air Force
Indian Air Force
Royal Jordanian Air Force
Japan Air Self-Defense Force (Designation: U-4)
Sultan Of Johor (Malaysia)
Mexican Navy
Royal Netherlands Air Force (Commander/Executive Transport)
United Arab Emirates (VIP Transport)
USA - National Oceanographic And Atmospheric Administration
United States Air Force
United States Army
United States Navy
United States Marine Corps