Armstrong Siddeley Snarler

Armstrong Siddeley Snarler

__NOTOC__ __NOEDITSECTION__infobox rocket engine
name=Snarler
country_of_origin=Britain
purpose=
type=liquid
fuel=methanol / water
oxidiser=Liquid oxygen (LOX)
manufacturer=Armstrong Siddeley
thrust=2,000lbf (8.9kN) cite web
title=United Kingdom Aerospace and Weapons Projects: Rocket Engines
url=http://www.skomer.u-net.com/projects/rocketengine.htm
publisher=Skomer
]
capacity=LOX 75 gallons (288 l),
water-methanol 120 gallons (460 l)

The Armstrong Siddeley Snarler was a small rocket engine used for combined-power experiments with an early jet engine. [cite journal
title=Rockets for Aircraft Propulsion
author=S. Allen
journal=The Aeroplane
date=7 Dec 1951
] A prototype of the P.1040 Sea Hawk, fitted with a Rolls-Royce Nene turbojet of 5,200 lbf thrust, had an additional rocket of 2,000 lbf thrust added. The combination was termed the Hawker P.1072. It was first used in flight on 20 November, 1950. Half a dozen flights were made using the rocket motor before a minor explosion damaged the aircraft. it was decided that reheat was a more practical proposition for boosting jet thrust than rockets.

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