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A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing ConditionsAn equation is presented for calculating the heat flow required from the surface of an internally heated windshield in order to prevent the formation of ice accretions during flight in specified icing conditions. To ascertain the validity of the equation, comparison is made between calculated values of the heat required and measured values obtained for test windshields in actual flights in icing conditions. The test windshields were internally heated and provided data applicable to two common types of windshield configurations; namely the V-type and the type installed flush with the fuselage contours. These windshields were installed on a twin-engine cargo airplane and the icing flights were conducted over a large area of the United States during the winters of 1945-46 and 1946-47. In addition to the internally heated windshield investigation, some test data were obtained for a windshield ice-prevention system in which heated air was discharged into the windshield boundary layer. The general conclusions resulting from this investigation are as follows: 1) The amount of heat required for the prevention of ice accretions on both flush- and V-type windshields during flight in specified icing conditions can be calculated with a degree of accuracy suitable for design purposes. 2) A heat flow of 2000 to 2500 Btu per hour per square foot is required for complete and continuous protection of a V-type windshield in fight at speeds up to 300 miles per hour in a moderate cumulus icing condition. For the same degree of protection and the same speed range, a value of 1000 Btu per hour per square foot suffices in a moderate stratus icing condition. 3) A heat supply of 1000 Btu per hour per square foot is adequate for a flush windshield located well aft of the fuselage stagnation region, at speeds up to 300 miles per hour, for flight in both stratus and moderate cumulus icing conditions. 4) The external air discharge system of windshield thermal ice prevention is thermally inefficient and requires a heat supply approximately 20 times that required for an internal system having the same performance.
Document ID
19930082066
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Jones, Alun R
(National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Holdaway, George H
(National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Steinmetz, Charles P
(National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
November 1, 1947
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-TN-1434
Accession Number
93R11356
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
ICE FORMATION
ICE PREVENTION - EXHAUST GAS HEATING
EQUATIONS - HEAT TRANSMISSION
HEAT TRANSMISSION - WINDSHIELDS
AIRPLANES - CURTISS C-46 - FLIGHT TESTS (AMER )
ICE PREVENTION - WINDSHIELDS, AIR-HEATED
ICE PREVENTION - WINDSHIELDS, ELECTRICALLY HEATED
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