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Heat Transfer of Airfoils and PlatesThe few available test data on the heat dissipation of wholly or partly heated airfoil models are compared with the corresponding data for the flat plate as obtained by an extension of Prandtl's momentum theory, with differentiation between laminar and turbulent boundary layer and transitional region between both, the extent and appearance of which depend upon certain critical factors. The satisfactory agreement obtained justifies far-reaching conclusions in respect to other profile forms and arrangements of heated surface areas. The temperature relationship of the material quantities in its effect on the heat dissipation is discussed as far as is possible at tk.e present state of research, and it is shown that the profile drag of heated wing surfaces can increase or decrease with the temperature increase depending upon the momentarily existent structure of the boundary layer.
Document ID
20050019473
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Seibert, Otto
Date Acquired
September 7, 2013
Publication Date
April 1, 1943
Publication Information
Publication: Jahrbuch 1938 der Deutschen Luftfahrtforschung
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-TM-1044
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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