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Turbulent Friction in the Boundary Layer of a Flat Plate in a Two-Dimensional Compressible Flow at High SpeedsIn the present report an investigation is made on a flat plate in a two-dimensional compressible flow of the effect of compressibility and heating on the turbulent frictional drag coefficient in the boundary layer of an airfoil or wing radiator. The analysis is based on the Prandtl-Karman theory of the turbulent boundary later and the Stodola-Crocco, theorem on the linear relation between the total energy of the flow and its velocity. Formulas are obtained for the velocity distribution and the frictional drag law in a turbulent boundary later with the compressibility effect and heat transfer taken into account. It is found that with increase of compressibility and temperature at full retardation of the flow (the temperature when the velocity of the flow at a given point is reduced to zero in case of an adiabatic process in the gas) at a constant R (sub x), the frictional drag coefficient C (sub f) decreased, both of these factors acting in the same sense.
Document ID
20050029417
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Frankl, F.
Voishel, V.
Date Acquired
September 7, 2013
Publication Date
December 1, 1943
Publication Information
Publication: Report of the Central Aero-Hydrodynamical Institute, Moscow
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NACA-TM-1053
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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