Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer PDF Download
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Author: Robert L. P. Voisinet
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 144
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Book Description
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
Author: Robert L. P. Voisinet
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 144
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Book Description
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
Author: Robert L. P. Voisinet
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 124
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Book Description
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
Author: David F. Gates
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 124
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Book Description
The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Author: Alan. L. Kistler
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 62
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Book Description
Author: Alvin Seiff
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 654
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Book Description
Heat-transfer data from four wind-tunnel experiments and two free-flight experiments with turbulent boundary layers have been examined to see whether or not they are well represented by the Reynolds analogy or a modification thereof. The heat-transfer results are put into the form of dimensionless Stanton numbers based on fluid properties at the outer edge of the boundary layer and are compared with skin-friction coefficients for the same Mach numbers and wall to free-stream temperature ratios as obtained from an interpolation of the existing skin-friction data. The effective Reynolds number is taken to be the length Reynolds number measured from the effective turbulent origin, a position which differs importantly from the leading edge of the test surface in some cases.
Author: James F. Schmidt
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 62
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Book Description
In order to provide a relatively simple heat-transfer prediction along a nozzle, a differential (similar-solution) analysis for the turbulent boundary layer is developed. This analysis along with a new correlation for the turbulent Prandtl number gives good agreement of the predicted with the measured heat transfer in the throat and supersonic regiono f the nozzle. Also, the boundary-layer variables (heat transfer, etc.) can be calculated at any arbitrary location in the throat or supersonic region of the nozzle in less than a half minute of computing time (Lewis DCS 7094-7044).
Author: Virgil A. Sandborn
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 168
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Book Description
Author: W. B. Sturek
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
Author: David L. Whitfield
Publisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 108
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Book Description
This report describes the results of analytical, numerical, and experimental investigations of incompressible and compressible boundary layers. The subjects considered are (1) Laminar and/or turbulent numerical boundary-layer calculations in which the Reynolds stress is related to the turbulent kinetic energy; (2) an analytical investigation of turbulence near a wall which is not founded on classical mixing-length theory; (3) analytical solutions for relating velocity and temperature throughout turbulent boundary layers for nonunity Prandtl numbers; (4) a description of the data reduction of pitot pressure measurements utilizing these analytical results, and (5) the application of the numerical and analytical results to the analysis of turbulent boundary-layer measurements made in the Propulsion Wind Tunnel Facility (PWT).
Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
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Book Description
Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author).
