U.S. Patent Specifications
Aircraft Engineering and Aerospace Technology
Article publication date: 1 March 1937
A radial, air cooled, aircraft engine, said engine including cylinders having parts carried by and extending beyond the heads thereof, and having cooling fins, a cowl of substantially streamline external configuration around said engine, including said head carried parts, and preventing radial airflow in the zone of the cylinders of said engine, said cowl having openings for entrance and exit of cooling air, such openings being a substantial distance forward and rearward respectively from the centre lines of the cylinders of said engine so as to minimize eddy formation by said cylinders, means disposed between said cylinder heads and said cowl substantially preventing air flow past said parts, and means, co‐operating with said first means and said cowl, to confine substantially the entire flow of said cooling air between the cooling fins of said cylinders.
(1937), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 9 No. 3, pp. 86-86. https://doi.org/10.1108/eb030164
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