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Title
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Heat Transfer and Frictional Effects in Laminar Boundary Layers. Part 4. Universal Series Solutions
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Date
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1954
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Index Abstract
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Not Available
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Photo Quality
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Not Needed
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Report Number
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WADC TR 53-288 Part 4
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Corporate Author
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Ohio State University Research Foundation
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Laboratory
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Aeronautical Research Laboratory
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Extent
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233
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Identifier
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AD0062281
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Access Rights
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Notice(s)
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Distribution Classification
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1
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Contract
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AF 33(038)-10834
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DoD Project
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1366
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DoD Task
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None Given
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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ASD ltr
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Abstract
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In Section 1 tables of values are obtained for universal functions applicable to the laminar velocity and thermal boundary layers occurring on an isothermal surface having symmetric, two-dimensional flow, i.e., a local free stream velocity distribution given by a series of odd powers of the distance from the forward stagnation point. Using some of these functions, it has been found that, for a Prandtl number of one, the friction coefficient in a linearly-increasing velocity field increases eleven percent as the local Mach number increases from 0 to 1.60. Equations defining universal functions applicable to the thermal boundary layer occurring in the flow field of Section 1 when the surface is not isothermal have been derived in Section II. Relationships between some of these functions and those of Section 1 have been determined. Section III presents velocity and thermal analyses of the laminar boundary layer on an isothermal surface subject to a local free stream velocity distribution expressible as a complete Taylor series. Equations have been derived defining applicable universal functions.
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Report Availability
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Full text available
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Date Issued
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1954-08
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Provenance
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Lockheed Martin Missiles & Fire Control
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Type
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report
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Format
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1 online resource
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Creator
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Tifford, Arthur N.
WADCTR53-288part04.pdf