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Improvements in Heat Transfer for Anti-Icing of Gas-Heated Airfoils with Internal Fins and PartitionsThe effect of modifying the gas passage of hollow metal airfoils by the additIon of internal fins and partitions was experimentally investigated and comparisons were made among a basic unfinned airfoil section and two airfoil designs having metal fins attached at the leading edge of the internal gas passage. An analysis considering the effects of heat conduction in the airfoil metal was made to determine the internal modification effectiveness that may be obtained in gas-heated components, such as turbojet-inlet guide vanes, support struts, hollow propeller blades, arid. thin wings. Over a wide range of heated-gas flow and tunnel-air velocity, the increase In surface-heating rates with internal finning was marked (up to 3.5 times), with the greatest increase occurring at the leading edge where anti-icing heat requirements are most critical. Variations in the amount and the location of internal finning and. partitioning provided. control over the local rates of surface heat transfer and permitted efficient anti-icing utilization of the gas-stream heat content.
Document ID
19810068608
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Gray, Vernon H.
(National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1950
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-TN-2126
Report Number: NACA-TN-2126
Accession Number
81N73030
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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