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a potential fire hazard if the system failed because of heater burnout. The alternative was a hot-gas system. If the large heating requirements associated with continuous hot-gas heating could be reduced by a cyclical system, ice could be removed without an increase in aircraft weight. A hot-gas cyclical system also had the advantages of integral design with the aircraft structure, low maintenance costs, and no fire hazards. For tests of the hot-gas cyclical de-icing system, researchers Gray, Bowden, and von Glahn used a NACA 65(1)-212 airfoil of 8-foot chord. The leading edge of the airfoil was heated by gas flow through chordwise passages in a double-skin construction similar to that found in a continuous gas-heating system. The airfoil also incorporated the parting strip that had been employed in the electric de-icing system experiments. The researchers subjected the model to a wide range of conditions. They used air- speeds of 180 and 280 miles per hour, angles of attack from 2° to 8°, air temperatures of -11° to 20°F, and liquid water content of 0.3 to 1.2 grams per cubic meter. To melt the ice, they employed high-pressure heated air, regulating the temperature by adding cold air, and controlling the pressure by means of a pressure-regulating valve. Gas temperature at the inlet of the supply duct ranged from 200° to 510°F. Their investigation revealed that the ice could be removed satisfactorily with cycle ratios (total cycle time divided by heat-on periods) of 10 to 26. “For minimum runback, efficient ice removal, and minimum total heat input,” they concluded, “short heat-on periods of about 15 seconds with heat-off periods of 260 seconds gave the best results.” Savings in heat over continuous anti-icing system requirements were considerable.19 The final phase of the investigation involved a comparative study of several methods of cyclic gas-heating systems. Researchers Gray and Bowden again used as their model a NACA 65(1)-212 airfoil with a 6-foot span, 8-foot chord, and a maximum thickness of 11.5 inches. They tested three systems that differed mainly in the way that they obtained elevated gas temperatures at the leading edge and in their use of parting strips. One system used a double-duct return-flow gas supply arrangement with spanwise and chord- wise parting strips. A second system was similar to the first one but without the parting strips. The third system featured a single-duct non-return gas supply arrangement and no parting strips. The first system gave the best results. Gray and Bowden found that 50 percent longer heat-on periods were required for systems without parting strips. They also dis- covered that the single-passage gas-supply duct system needed an 85 percent longer heat-on period than did the dual-duct systems. Overall, heat source requirements for A Golden Age 19 Gray, Bowden, and von Glahn, “Preliminary Results of Cyclical De-Icing of a Gas-Heated Airfoil,” NACA RM E51J29 (1952). 53PDF Image | History of NASA Icing Research Tunnel
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