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Heat Transfer and Frictional Effects in Laminar Boundary Layers. Part 4. Universal Series Solutions

Report Number: WADC TR 53-288 Part 4
Author: Tifford, Arthur N.
Corporate Author: Ohio State University Research Foundation
Laboratory: Aeronautical Research Laboratory
Date of Publication: 1954-08
Pages: 233
Contract: AF 33(038)-10834
Project: 1366
AD Number: AD0062281

Abstract:
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.


Provenance:
Lockheed Martin Missiles & Fire Control
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