Velocity Profile, Skin-friction Balance and Heat-transfer Measurements of the Turbulent Boundary Layers at Mach 5 and Zero-pressure Gradient PDF Download
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Author: Roland E. Lee
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 114
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Book Description
The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 68
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Book Description
A review of a comprehensive experimental investigation of the heat transfer and boundary layer in 30 deg to 15 deg and 60 deg to 15 deg conical nozzles is presented. The experiments were conducted with air at a stagnation temperature of 539 K (970 R) and throat Reynolds numbers based on a diameter ranging from 6 x 10 to the 5th power to 5 x 10 to the 6th power. Nozzle wall surface finish was varied from a smooth machine finish to a 826 x 10 to the minus 6th power cm (325 x 10 to the minus 6th in.) rms sandblasted finish. Measured heat transfer and wall temperatures are tabulated.
Author: Roland E. Lee
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 114
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Book Description
The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
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Book Description
Author: Suhas V. Patankar
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 248
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Book Description
Author: Hermann Schlichting (Deceased)
Publisher: Springer
ISBN: 366252919X
Category : Technology & Engineering
Languages : en
Pages : 814
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Book Description
This new edition of the near-legendary textbook by Schlichting and revised by Gersten presents a comprehensive overview of boundary-layer theory and its application to all areas of fluid mechanics, with particular emphasis on the flow past bodies (e.g. aircraft aerodynamics). The new edition features an updated reference list and over 100 additional changes throughout the book, reflecting the latest advances on the subject.
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:
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 580
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Book Description
Author: Donald M. Wilson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 94
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Book Description
Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
Author: A. A. R. Townsend
Publisher: Cambridge University Press
ISBN: 9780521298193
Category : Mathematics
Languages : en
Pages : 450
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Book Description
Develops a physical theory from the mass of experimental results, with revisions to reflect advances of recent years.
Author: Paige B. Burbank
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 430
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Book Description
