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.


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 length9.07 m (29 ft 9 in)
Height4.11m (13 ft 6 in)
Rotor disc168.11 m2 (1,809.6 sq ft)
Weight empty964 kg (2,125 lb)
Max T-O weight2,041 kg (4,500 lb)
Max disc loading12.14 kg/m2 (2.49 lb/sq ft)
Max power loading6.52 kg/kW (10.71 lb/shp)
PERFORMANCE (estimated):  
Never-exceed speed (VNE) 147 kt (273 km/h; 170 mph)
Cruising speed104 kt (193 km/h; 120 mph)
Service ceiling4,875 m (16,000 ft)
Range at 50% power 360 n miles (667 km; 415 miles)
Endurance 2 h 58 min