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Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer

Author : Robert L. P. Voisinet

Publisher :

Page : 144 pages

File Size : 14,74 MB

Release : 1973

Category : Fluid mechanics

ISBN :

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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).



Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer

Author : Robert L. P. Voisinet

Publisher :

Page : 124 pages

File Size : 15,92 MB

Release : 1973

Category : Fluid mechanics

ISBN :

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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).



Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers

Author : David F. Gates

Publisher :

Page : 124 pages

File Size : 43,62 MB

Release : 1973

Category : Supersonic nozzles

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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).





Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy

Author : Alvin Seiff

Publisher :

Page : 654 pages

File Size : 13,82 MB

Release : 1954

Category : Aerodynamics, Supersonic

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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.



Similar Solutions for Turbulent Boundary Layer with Large Favorable Pressure Gradients (nozzle Flow with Heat Transfer)

Author : James F. Schmidt

Publisher :

Page : 62 pages

File Size : 31,41 MB

Release : 1971

Category : Nozzles

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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).







Boundary Layer Transition at Supersonic Speeds

Author : E. R. Van Driest

Publisher :

Page : 108 pages

File Size : 31,13 MB

Release : 1961

Category : Aerodynamics, Supersonic

ISBN :

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Book Description

Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.