Hawker P.1072

Role: experimental aircraft
Manufacturer: Hawker
First flight: 20 November 1950
Number built: 1
Developed from: Hawker Sea Hawk

The Hawker P.1072 was a 1949 experimental British aircraft acting as test bed for the Armstrong Siddeley Snarler rocket booster. It was the prototype Hawker Sea Hawk modified to install the rocket in the tail.

Development

After World War II Hawker was working on a new fighter under their internal designation P.1040 which would later become the Hawker Sea Hawk.

Armstrong Siddeley had begun work in 1946 to develop a liquid-fuelled rocket motor (to be used as a booster unit for fighters) for the Ministry of Supply. To investigate the feasibility of rocket-powered fighter aircraft, the original Sea Hawk prototype, VP401, was converted into a test bed for the Armstrong Siddeley Snarler rocket motor along with a Rolls-Royce Nene turbojet becoming the P.1072. The P.1040 had a split exhaust which gave space in the tail free for the installation of the rocket.

The Snarler was pump fed rather than by pressurization of the fuel tanks. The installation of the rocket motor required considerable reinforcement of the fuselage as well as completely revised pneumatic and fuel systems. Jet engine fuel capacity was reduced from 395 gal (1,520 l) to 175 gal (675 l) and two tanks for rocket fuel were installed. The cylindrical liquid oxygen tank in the forward fuselage had a capacity of 75 gal (288 l), and the water-methanol tank in the rear fuselage had a capacity of 120 gal (460 l). External differences were limited to a slight bulge in the rear fuselage under the rudder and a fairing on the bottom centerline of the fuselage,covering piping between the tanks and the rocket motor in the tail.

The Rolls-Royce Nene 103 with 5,180 lbf (23.1 kN) of thrust was used for the ferry flights and for takeoff and initial climb. The Snarler rocket which developed 2,000 lbf (8.9 kN) of thrust was first used in flight on 20 November 1950. There were limitations on the Six flights were made using the rocket motor before a minor explosion damaged the aircraft. Soon after, the British government decided that turbojets with reheat (afterburner) would be used instead of rocket power.

Specifications (P.1072)

Data from British Aircraft Directory

General characteristics

Crew: 1
Length: 37 ft 7 in (11.46 m)
Wingspan: 36 ft 6 in (11.13 m)
Height: 8 ft 9 in (2.67 m)
Wing area: 264.7 ft² (24.6 m²)
Empty weight: 11,050 lb (approx. 5,000 kg)
Loaded weight: 14,500 lb ()
Powerplant:
1x— Rolls-Royce Nene 103 turbojet, 5,180 lbf (23.1 kN)
1x— Armstrong Siddeley Snarler ASSn.1 rocket, 2,000 lbf (8.9 kN)

Performance

Maximum speed: 553 mph (890 km/h)
Cruise speed: 447 mph (720 km/h)
Range: 350 mi (560 km)
Service ceiling: 44,500 ft ()
Rate of climb: 5,000 ft/min (25 m/s)
Wing loading: 53 lb/ft² (258 kg/m²)
Thrust/weight (jet): 0.51
Rocket Endurance: 2 minutes 45 seconds

Saunders-Roe SR.53

Hannah, Donald. Hawker FlyPast Reference Library. Stamford, Lincolnshire, UK: Key Publishing Ltd., 1982. ISBN 0-946219-01-X.
James, Derek N. Hawker, an Aircraft Album No. 5. New York: Arco Publishing Company, 1973. ISBN 0-668-02699-5. (First published in the UK by Ian Allan in 1972)
Mason, Francis K. Hawker Aircraft since 1920. London: Putnam, 1991. ISBN 0-85177-839-9 (reprinted as ISBN 1-55750-351-6.)

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Source: WikiPedia