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Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow

Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow
Author: Maurice Tucker
Publisher:
Total Pages: 30
Release: 1951
Genre: Aerodynamics, Supersonic
ISBN:

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An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.


Handbook of Supersonic Aerodynamics

Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
Total Pages: 364
Release: 1966
Genre: Aerodynamics, Supersonic
ISBN:

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Interacting Supersonic Turbulent Boundary Layers Over a Two-dimensional Protuberance

Interacting Supersonic Turbulent Boundary Layers Over a Two-dimensional Protuberance
Author: Arnold Polak
Publisher:
Total Pages: 38
Release: 1974
Genre: Aerodynamic heating
ISBN:

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The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author).


A Determination of the Laminar-, Transitional-, and Turbulent-boundary-layer Temperature-recovery Factors on a Flat Plate in Supersonic Flow

A Determination of the Laminar-, Transitional-, and Turbulent-boundary-layer Temperature-recovery Factors on a Flat Plate in Supersonic Flow
Author: Jackson R. Stalder
Publisher:
Total Pages: 20
Release: 1950
Genre: Plates (Engineering)
ISBN:

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The temperature-recovery factors have been measured on a flat plate in an air stream at a Mach number of 2.4, and a Reynolds number range from235,000 to 6,750,000. The recovery factor for a laminar boundary layer on a flat plate was found to be equal to 0.881. The corresponding value for a fully developed turbulent boundary layer resulting from natural transition varied from 0.897 to 0.884 along the plate. The maximum possible error in measurement of these values of recovery factor is estimated as plus or minus 0.007.


WADC Technical Report

WADC Technical Report
Author: United States. Wright Air Development Division
Publisher:
Total Pages: 1286
Release: 1955
Genre: Aeronautics
ISBN:

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Technical Note

Technical Note
Author:
Publisher:
Total Pages: 604
Release: 1952
Genre: Aeronautics
ISBN:

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