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Hawker Siddeley P.1154

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The Hawker Siddeley P.1154 was a supersonic VSTOL fighter aircraft being developed alongside the subsonic Hawker Siddeley P.1127/Kestrel. The project was cancelled in 1965.


The project came about as a possible aircraft for use both with the Royal Air Force and the Royal Navy. It would replace the Hawker Hunter in the RAF and the de Havilland Sea Vixen in the Fleet Air Arm (FAA). The RAF requirement was for a single seat fighter, the RN a two seat interceptor. Accordingly the design started to diverge with the naval version being the P.1154RN.

Propelled by a single Bristol Siddeley BS100 vectored thrust turbofan, the aircraft would have reached supersonic flight speeds from the thrust boost obtained by igniting the engine's PCB (Plenum Chamber Burning) system. Rolls-Royce offered a PCB, vectored thrust twin-Spey design as an alternative.

The P.1154 came out equal winner in a NATO run competition with the Dassault Mirage IIIV, a separate lift/thrust engine concept. The P.1154 was adjudged technically superior but the Mirage gained points for the scope for cooperative development and production across member nations.

With the RAF and RN requirements diverging, the aircraft was looking less viable. The RN cancelled their interest in 1963, removing the need to meet the requirements of both services, and work on the RAF P.1154 prototype started. However, the following year the government cancelled the P.1154 along with the BAC TSR-2 and Hawker Siddeley HS.681. Following the cancellation, the RAF and RN adopted the F-4 Phantom II instead, but the government also gave a contract for continued work on the P.1127(RAF), which led to the Harrier.

Specifications (P.1154)

Data from Specification SR250D, October 1964

General characteristics

  • Crew: One
  • Length: 57 ft 6 in (17.53 m)
  • Wingspan: 28 ft 4 in (8.64 m)
  • Height: 12 ft 6 in (3.81 m)
  • Wing area: 269 ft² (25 m²)
  • Empty weight: 20,100 lb (9,136 kg)
  • Max takeoff weight: 40,050 lb (18,204 kg)
  • Powerplant:Bristol Siddeley BS100/8 Phase II vectored-thrust turbofan engine with PCB
    • Dry thrust: 26,200 lbf (117 kN)
    • Thrust with afterburner: 33,900 lbf (151 kN)
  • * Internal fuel: 1,300 Imperial gallons (5,910 litres)


  • Maximum speed: Mach 1.13 at sea level / Mach 1.7 at altitude (860-1,294 mph / 1,384-2,082 km/h)
  • Range: 420 to 560 nm depending on speed and load (483-644 miles / 778-1,037 km)


  • Each wing: two pylons, (2,000 lb (909 kg) inboard, 1,000 lb (454 kg) outboard)
  • Fuselage: single centreline pylon (2,000 lb) or 2 pylons at 1,000 lb each
  • Weapons: Mix of Matra SNEB rockets, anti-radar AJ.168 missile, Red Top missiles, 2-inch rockets, 30 mm ADEN cannon.

See also

Related development

Comparable aircraft


External links

Template:Hawker Aircraft aircraft Template:Harrier variants

Template:UK-mil-stub ja:ホーカー・シドレー P.1154

This article is licensed under the GNU Free Documentation License.
It uses material from the Wikipedia article "Hawker Siddeley P.1154".