Dassault Falcon 5X
| Falcon 5X | |
|---|---|
 |
|
| June 2, 2015 roll-out | |
| Role | Business jet |
| National origin | France |
| Manufacturer | Dassault Aviation |
| First flight | 2017 (scheduled) |
| Introduction | 2020 (scheduled) |
| Status | Under development[1] |
| Number built | 0 |
| Unit cost | |
The Dassault Falcon 5X is a large, long-range business jet under development in France by Dassault Aviation.[3]
Even though its projected Lua error in Module:Convert at line 1851: attempt to index local 'en_value' (a nil value). range is not as high as that of the Falcon 7X, the 5X has a larger fuselage diameter and greater cabin volume.[4] On 29 January 2016, Dassault Aviation confirmed a two-year delay and production freeze on the Falcon 5X because of ongoing problems with the Snecma Silvercrest engine ; the first flight is scheduled to take place in 2017, with an entry into service in 2020.[1]
Design and development
Design work began in 2006 under the codename SMS for super-midsize, and was envisioned to compete with the Hawker 4000, the Bombardier Challenger 300 and the Gulfstream G200 or the Embraer Legacy 600 with a 3400 nm range but few details were given except it were to be powered by two 10,000-pound-thrust Rolls-Royce RB282.[2][5] In 2009 design choices have been reopened and the engine evaluation process was re-opened.[6]
The project was revamped after the 2008 recession when demand for super midsized and smaller aircraft fell down, but the large-cabin, long-range stayed high enough. It was unveiled at the National Business Aviation Association annual convention in October 21, 2013.[2] The aircraft is now planned to be powered by two Snecma Silvercrests.[4] The cabin will also feature an unusual "zenith window" in the roof, allowing more light to come in.[3]
Specifications
Data from Flight International 2013[7]
General characteristics
- Crew: 3
- Capacity: 16
- Length: 25.2 m (82 ft 8 in)
- Wingspan: 25.9 m (85 ft 0 in)
- Height: 7.5 m (24 ft 7 in)
- Max takeoff weight: 31,570 kg (69,600 lb)
- Maximum landing weight: 29,980 kilograms (66,095 lb)
- Maximum zero fuel weight: 22,790 kilograms (50,243 lb)
- Powerplant: 2 × Snecma Silvercrest , 50.9 kN (11,450 lbf) thrust each
Performance
- Maximum speed: 956 km/h; 594 mph (516 kn) at cruising altitude
- Maximum speed: Mach 0.90
- Range: 9,630 km; 5,984 mi (5,200 nmi) with 8 passagers + 3 crew, NBAA IFR reserves, ISA, full fuel, mach 0.8
- Service ceiling: 15,545 m (51,000 ft)
- Balanced field length: 5,250ft (MTOW, SL, ISA)
- Approach speed (Vref): 105kts ias (Typical landing weight, SL)
See also
- Aircraft of comparable role, configuration and era
- Related lists
References
- ↑ 1.0 1.1 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 2.0 2.1 2.2 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 3.0 3.1 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 4.0 4.1 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ Lua error in package.lua at line 80: module 'strict' not found.
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External links
- Manufacturer specifications
- Lua error in package.lua at line 80: module 'strict' not found.
