TYPE: Utility autogyro.
PROGRAMME: Technology demonstrator development of Hawk 4. Will not be marketed. Announced late 2000 as Hawk 6G with an expected first flight (prototype N9112A) in January 2001; first flight eventually made 22 September 2001. Based around Cessna 337 fuselage with single 335 kW (420 shp) Rolls-Royce 250-B17F2 turboprop in nose for propulsion, driving FC9684C-6RX three-blade propeller; Rolls-Royce 250-C18 above fuselage for rotation; inverted Cessna 337 tailplanes and shortened wing with spoilers and two-blade rotor system from Hawk 4. Estimated cruising speed 113 to 130 kt (209 to 241 km/h; 130 to 150 mph); useful load 907 kg (2,000 lb).
COSTS: US$950,000 (2003).
DESIGN FEATURES: Basically similar to Hawk 4.
FLYING CONTROLS: Broadly similar to Hawk 4.
STRUCTURE: As Hawk 4.
POWER PLANT: Powered by a 335 kW (420 shp) Rolls-Royce 250-C18 turboprop engine. Fuel capacity 416 litres (110 US gallons; 91.6 Imp gallons). External tanks mounted at wingtips are modified Piper PA-24 Comanche wingtip units.
AVIONICS: Instrumentation: Full IFR.
|Rotor diameter||13.41 m (44 ft 0 in)|
|Fuselage length||9.07 m (29 ft 9 in)|
|Height||4.11m (13 ft 6 in)|
|Rotor disc||168.11 m2 (1,809.6 sq ft)|
|WEIGHTS AND LOADINGS (estimated):|
|Weight empty||964 kg (2,125 lb)|
|Max T-O weight||2,041 kg (4,500 lb)|
|Max disc loading||12.14 kg/m2 (2.49 lb/sq ft)|
|Max power loading||6.52 kg/kW (10.71 lb/shp)|
|Never-exceed speed (VNE)||147 kt (273 km/h; 170 mph)|
|Cruising speed||104 kt (193 km/h; 120 mph)|
|Service ceiling||4,875 m (16,000 ft)|
|Range at 50% power||360 n miles (667 km; 415 miles)|
|Endurance||2 h 58 min|