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To prevent the formation of ice on aircraft, the air‐stream for cooling the engine enters through a diverging inlet and after becoming heated by the engine, which may be of either air‐cooled or liquid‐cooled type, passes along conduits, at the leading edges of the wings or at other parts, and leaves by converging outlets. The kinetic energy of the stream is thus first converted into pressure energy and then reconverted to kinetic energy, the air heated by the engine or radiator being taken from a point at low pressure and velocity. Air enters at diverging inlets 13 above the two engines, and after passing over the radiators 11 passes by converging conduits 14, 15 to outlets 17, IS. In Fig. 4 (not shown), the aircraft has a single engine in the nose with a single radiator below it, and in Fig. 6 (not shown) a single engine has two radiators. The engine oil‐cooler, if provided, may also be situated in the passage.