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Month in the Patent Office

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 December 1936



The radiator b of a liquid‐cooled aircraft engine is housed in a tunnel‐like cowling bl, through which the slip stream flows by a contracted entrance and exit b3, b6 and into which the exhaust is discharged by nozzles ƒ; the exhaust system thus has less drag on the aircraft, and the air flow past the radiator is increased. The radiator is of horseshoe shape in cross‐section, and inclined and Venturi‐shaped slats b4, ƒ1 are provided to steady the air flow and to act as silencers and flame dampers, The exhaust may be led by D‐sectioned pipes d1 arranged within the contour of the cowling, but separated therefrom by a cooling‐air space. Alternatively the pipes may be circular and located inside the cowling ; they are surrounded by jackets through which air is led by diverging intakes in the air stream and from which it is discharged behind the radiator. An oil cooler g is arranged in the cowling underneath the radiator. The two exhaust pipes of a V‐engine extend down the two sides of the cowling and are united to the pipe having the nozzles ƒ.


(1936), "Month in the Patent Office", Aircraft Engineering and Aerospace Technology, Vol. 8 No. 12, pp. 349-350.




Copyright © 1936, MCB UP Limited

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