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Comparison of Heat Transfer from Airfoil in Natural and Simulated Icing ConditionsAn investigation of the heat transfer from an airfoil in clear air and in simulated icing conditions was conducted in the NACA Lewis 6- by 9-foot icing-research tunnel in order to determine the validity of heat-transfer data as obtained in the tunnel. This investiation was made on the same model NACA 65,2-016 airfoil section used in a previous flight study, under similar heating, icing, and operating conditions. The effect of tunnel turbulence, in clear air and in icingwas indicated by the forward movement of transition from laminar to turbulent heat transfer. An analysis of the flight results showed the convective heat transfer in icing to be considerably different from that measured in clear air and. only slightly different from that obtained in the icing-research tunnel during simulated icing.
Document ID
19810068712
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Gelder, Thomas F. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Lewis, James P. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
September 1, 1951
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NACA-TN-2480
Accession Number
81N73134
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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