W-6 Manx

W-6 Manx Class

The W-6 is a limited-VTOL-capable aerospace vehicle, in so far as it has conventional flight surfaces but is also capable of ascending beyond the atmosphere, maneuvering in orbit and re-entering under its own power.

The protected downward main-engine outlets are available on request wherever aerodynamic loading permits, including high altitude and orbit. Door protection uses dynamic pressure: downward flow is inhibited above 4,000 Pa, and can re-enable below 3,200 Pa. There is no separate speed, altitude or vacuum cutoff. The doors take about 0.6 seconds to open, and must be fully open before downward thrust starts. Forward, reverse and downward flow share each engine's existing thrust budget. See VTOL operating envelope for sequencing, pressure hysteresis and orbital braking considerations.

In STOVL operation, one underside outlet on each engine carries the downward flow. These two outlets share the existing total main-engine thrust. At full downward output, no forward or reverse thrust remains available from those engines.

Statistics

W-6 Manx — Aerospace vehicle specifications

General
Manufacturer	Trimbal-Kneers Aerospace	Type / role	Aerospace vehicle
Price / MSRP	3,989,373 CR	Availability	Not specified
Restrictions	Not specified	IVR series	Not specified
Dimensions and weights
Length	44.9 m	Width	Not specified
Height	9.4 m (with gear)	Empty / curb weight	50,000 kg (BOW)
Fuel capacity	12,000 kg (Iagreous)	Payload	43,009 kg
Maximum gross / takeoff weight	105,009 kg (gross)
Capacity and equipment
Seats	Not specified	Passenger capacity	6 in Bay 0 instead of cargo
Cargo bays	3	Cargo capacity	Not specified
Internal stowage	7 MT (Bay 0), or 6 passengers	Avionics bays	4
Weapon mounts	1	Engine count	2
Life support
Cabin pressurization	Pressurized — stored breathing gas	Rated pressure differential	2,400 mbar (240 kPa), cabin above surroundings
Performance
Engine / propulsion	Not specified	Maximum speed	94 m/s IAS at MSL
Normal range	Indefinite (capable of reaching orbit)	Endurance	Not specified
Flight
Wingspan	50.1 m	Effective wing area	640.965 m2
Cruising speed	539 m/s at 15 km	Service ceiling	Indefinite (capable of reaching escape velocity)
Engine critical altitude	Not specified	Bypass ratio	Not specified
Thrust	1,029,779 N total forward/reverse in vacuum (514,890 N per engine); about 947,397 N total at reference sea-level density	Maximum acceleration	Main thrust alone at maximum gross: 9.807 m/s² in vacuum, 9.022 m/s² at reference sea-level density; before drag and gravity
VTOL capability	Limited	Rain Protection Type	Bleed air system
Flight controls and landing gear
Flight Spoilers	Not specified	Ground Lift Dump (GLD)	Not specified
Retractable Landing Gear	Not specified	Landing Gear Type	Wheels, three strut groups
Touchdown descent design limit	10 ft/s (3.048 m/s; 600 ft/min), at maximum gross mass with healthy, fully deployed gear and balanced contact on a firm, level surface	Crosswind component limit	Not established; this is not an unlimited-crosswind rating
Leading Edge Flaps	Not specified	Trailing Edge Flaps	Not specified
Space operations
Orbital capability	Capable of reaching orbit and escape velocity	Interstellar capability	Not specified
Docking / interfaces	Not specified

The descent design value is a structural reference, not a target landing rate. Uneven contact, damaged gear and excess mass reduce the landing margin. Braking and sideways tire forces share the available surface grip; skidding alone does not mean a strut has failed.

Standard Equipment

• GPWS
• VMU engine-failure warnings and flap-position confirmations.
• Trailing-edge flap detents at 0°, 8°, 20°, 30° and 40°. The default bindings are Shift+F8 to extend one detent and Shift+F9 to retract one detent; custom bindings may differ. The VMU confirms the selected detent when the flaps reach it, in either direction.
• Autoflyte
• VTOL
• 320 km LRS with TCAS

External Links

• Detailed specifications