1. Development

2. Specifications (P.1072)

3. See also

4. Notes

5. References

6. External links

The Hawker P.1072 was a 1949 experimental British aircraft acting as test bed for the Armstrong Siddeley Snarler rocket booster engine. 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 later became 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,^[2] in addition to its normal 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)

|crew=1
|length ft=37
|length in=7
|span ft=36
|span in=6
|height ft=8
|height in=9
|wing area sqft=264.7
|aspect ratio=
|airfoil=
|empty weight lb=11050
|gross weight lb=14500
|max takeoff weight kg=
|max takeoff weight lb=
|max takeoff weight note=
|fuel capacity=Turbine fuel: {{cvt|175|impgal|USgal l}}; Rocket oxidiser: {{cvt|75|impgal|USgal l}}; Rocket fuel: {{cvt|120|impgal|USgal l}}
|more general=

|eng1 number=1
|eng1 name=Rolls-Royce Nene 103
|eng1 type=centrifugal flow turbojet
|eng1 lbf=5180
|eng1 note=main engine
|eng2 number=1
|eng2 name=Armstrong Siddeley ASSn.1 Snarler
|eng2 type=liquid-fuelled rocket
|eng2 lbf=2000
|eng2 note=endurance: 2 minutes 45 seconds

|max speed mph=553
|cruise speed mph=447
|stall speed kmh=
|stall speed mph=
|stall speed kts=
|stall speed note=
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|range miles=350
|endurance=
|ceiling ft=44500
|g limits=
|roll rate=
|climb rate ftmin=5000
|time to altitude=
|wing loading lb/sqft=53
|wing loading note=
|fuel consumption kg/km=
|fuel consumption lb/mi=
|thrust/weight={{cvt|0.51|lbf/lb}}
|more performance=
}}

See also

• Saunders-Roe SR.53

Notes

References

• 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}}.)

External links

• [https://web.archive.org/web/20070930180612/http://www.britishaircraft.co.uk/aircraftpage.php?ID=502 Hawker P.1072] – British Aircraft Directory

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