Experimental Investigation of Supersonic Boundary Layer Including Favorable Pressure Gradient Effects
Author: Joel J. Luker
Publisher:
Published: 1995
Total Pages: 0
ISBN-13:
DOWNLOAD EBOOKRead and Download eBook Full
Author: Joel J. Luker
Publisher:
Published: 1995
Total Pages: 0
ISBN-13:
DOWNLOAD EBOOKAuthor: Joel J. Luker
Publisher:
Published: 1995
Total Pages: 392
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DOWNLOAD EBOOKAuthor: Chad S. Hale
Publisher:
Published: 1995
Total Pages: 0
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DOWNLOAD EBOOKAuthor: James Frederick Johnson
Publisher:
Published: 1978
Total Pages: 226
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DOWNLOAD EBOOKAuthor: Chad S. Hale
Publisher:
Published: 1995
Total Pages: 280
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DOWNLOAD EBOOKAuthor: Walter B. Sturek
Publisher:
Published: 1971
Total Pages: 382
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DOWNLOAD EBOOKAuthor: Edward Gootzait
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Published: 1976
Total Pages: 322
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DOWNLOAD EBOOKAuthor: S. Sivasegaram
Publisher:
Published: 1969
Total Pages:
ISBN-13: 9780114704582
DOWNLOAD EBOOKAuthor: S. Sivasegaram
Publisher:
Published: 1971
Total Pages: 19
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DOWNLOAD EBOOKAuthor: Walter B. Sturek
Publisher:
Published: 1970
Total Pages: 129
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DOWNLOAD EBOOKExperimental measurements of the profile characteristics of the supersonic turbulent boundary layer in a region of zero pressure gradient and in a region of moderate adverse pressure gradient along the curved surface of an isentropic ramp model are reported. Detailed surveys of impact pressure, static pressure and total temperature were taken through the boundary layer and local values of wall shear stress were obtained using the Preston tube technique. The measurements were made in a supersonic wind tunnel for a nominal tunnel nozzle setting of Mach 3.5. The data are for an adiabatic wall with values of momentum thickness Reynolds number ranging from 19,000 to 42,000. The experiment is described in detail and the mean profile data are presented in tabular form. Fluctuation data obtained using constant temperature hot wire anemometry are presented for one station in the region of zero pressure gradient and for one station in the region of adverse pressure gradient. (Author).