TYPE: Supersonic business jet.

PROGRAMME: Initial studies (Design Cycle 1) between December 2003 and September 2004; announced at NBAA Convention in Las Vegas on 11 October 2004; detailed Design Cycle 2 begun September 2004 and included wind-tunnel tests and marketing survey; Design Cycle 2 — final element of Phase I completed by September 2005, eliminating T-tail of earlier studies, among other improvements; expected five-year programme from launch (2007 or 2008) to certification.

CUSTOMERS: Estimated market for 250 to 300 aircraft over 10-year period, 30 to 50 per cent of orders expected to come from fractional ownership operators.

COSTS: Target price USD80 million. Estimated direct operating cost USD8 per mile (both 2004).

DESIGN FEATURES: Low-risk design using mostly established technology and not dependent for market viability upon repeal of legislation prohibiting supersonic flight over land. Low cruising speed of Mach 0.99, where required; ‘boomless’ cruise at Mach 1.1; max (unlimited) cruising speed Mach 1.6.
Fuselage has vertical oval cross-section in forward cabin, transitioning to oval in main cabin. Trapezoidal wing planform of natural laminar flow (NLF) section with rated wingtips; thickness 3% at root, 2% at tip. At supersonic cruise, achieves laminars flow over as much as 70 per cent of upper surface and up to whole lower surface. Cruciform tail with swept fin; area-ruled fuselage; engines pod-mounted on rear fuselage. Large trailing-edge flaps serve as flaperons for roll control (obviating spoilers) and are fitted with unique feature of secondary split flap at approximately half-chord to enhance low-speed capability and permit nose-down flight deck angle on landing approach; no leading-edge high-lift devices. Small notch in wing leading-edge at intersection with fuselage.

FLYING CONTROLS: Powered, electronically-signalled, hydraulically-actuated control surfaces. Flaps. Speedbrake.

STRUCTURE: Carbon fibre wings; high-strength aluminium alloy fuselage.

LANDING GEAR: Tricycle type; retractable. Two wheels in tandem on main units, twin wheels on nose unit. Ground turning radius less than 22.8 m (75 ft).

POWER PLANT: Two Pratt & Whitney JT8D-219 turbofans, each flat rated at 87.2 kN (19,600 lb st), with modified fan, upgraded compressor section and new exhaust mixer nozzle; low take-off thrust rating will enable the aircraft to meet Stage IV noise requirements. Thrust reverser. Fixed geometry scarfed air intakes. Fuel contained in wing and fuselage tanks.

ACCOMMODATION: Flat floor cabin with typical accommodation for 10 passengers, with two individual seats forward and two sets of club four seats aft; maximum 12 passengers; 11 cabin windows per side; galley at front and lavatory and baggage compartment at rear of cabin. Door forward, to rear of flight deck.

SYSTEMS: Stability augmentation system; pilot's commands are signalled to control surfaces electronically, but absence of AFCS and positive stability mean aircraft is not FBW in full sense. Tailplane size permits full control by pilot in the event of stability augmentation system failure. Cabin pressurisation system will have maximum pressure differential of 0.55 to 0.69 bar (8 to 10 lb/sq in).

DIMENSIONS, EXTERNAL:

• Wing span: 19.56 m (64 ft 2 in)
• Wing aspect ratio: 3.3
• Length overall: 41.30 m (135 ft 6 in)
• Height overall: 6.45 m (21 ft 2 in)

DIMENSIONS, INTERNAL:

• Cabin (cockpit divider to aft pressure bulkhead):
• Length: 9.l4 m (30 ft 0 in)
• Max width: 1.98 m (6 ft 6 in)
• Max height: 1.83 m (6 ft 0 in)
• Volume: 27.75 m³ (980.0 cu ft)

AREAS:

• Wings, gross: 111.48 m² (1,200 sq ft)

WEIGHTS AND LOADINGS:

• Basic operating weight: 20,457 kg (45,100 lb)
• Max fuel weight: 20,593 kg (45,400 lb)
• Max T-O weight: 40,823 kg (90,000 lb)
• Max wing loading: 366.2 kg/m² (75.00 lb/sq ft)
• Max power loading: 255 kg/kN (2.50 lb/lb st)

PERFORMANCE (at max T-O weight, ISA, except where indicated):

• Max cruising speed: M1.60
• Long-range cruising speed: M1.50
• No-boom cruising speed: more than M1.10
• High subsonic cruising speed: M0.99
• Long-range subsonic cruising speed: M0.95
• Approach speed: 120 kt (222 km/h; 138 mph)
• Max operating altitude: 15,545 m (51,000 ft)
• T-O balanced field length: less than 1,829 m (6,000 ft)
• Landing run, wet runway: less than 1,524 m (5,000 ft)
• Range with NBAA IFR reserves, subsonic or supersonic: more than 4,000 n miles (7,408 km; 4,603 miles)