NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
Description of the design and an outline of the method of design analysis is given for a thermal ice-prevention system for the B-24D airplane. The thermal ice-prevention system is based upon raising the temperature of the surfaces to be protected from ice formations by subjecting the inner face of the surface to a stream of heated air. The sources of heated air are four exhaust gas-air heat exchangers, one on each engine. The heated air is caused to circulate by the dynamic pressure of the air stream. A design analysis is given in general form, as a possible outline for future computations. It was concluded that this thermal ice-prevention equipment for the B-24D airplane wings, empennage, and windshield is structurally feasible and that installation will probably satisfy all design requirements.