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Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic FlowCalculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
Document ID
19810068583
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Callaghan, Edmund E.
(National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Serafini, John S.
(National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1953
Subject Category
Aerodynamics
Report/Patent Number
NACA-TN-2861
Report Number: NACA-TN-2861
Accession Number
81N73005
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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