A Flight Investigation of the Transonic Area Rule for a 52.5© Sweptback Wind-body Configuration at Mach Numbers Between 0.8 and 1.6
Author: Sherwood Hoffman
Publisher:
Published: 1954
Total Pages: 30
ISBN-13:
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Author: Sherwood Hoffman
Publisher:
Published: 1954
Total Pages: 30
ISBN-13:
DOWNLOAD EBOOKAuthor: Sherwood Hoffman
Publisher:
Published: 1953
Total Pages: 24
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DOWNLOAD EBOOKAuthor: William E. Palmer
Publisher:
Published: 1956
Total Pages: 40
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DOWNLOAD EBOOKAuthor: Robert L. Nelson
Publisher:
Published: 1957
Total Pages: 52
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DOWNLOAD EBOOKSummary: The experimental wave drags of bodies and wing-body combinations over a wide range of Mach numbers are compared with the computed drags utilizing a 24-term Fourier series application of the supersonic area rule and with the results of equivalent-body tests.
Author: Sherwood Hoffman
Publisher:
Published: 1958
Total Pages: 27
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DOWNLOAD EBOOKAuthor: Louis S. Stivers
Publisher:
Published: 1960
Total Pages: 32
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DOWNLOAD EBOOKAuthor: Lana M. Couch
Publisher:
Published: 1973
Total Pages: 116
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DOWNLOAD EBOOKExperimental data were obtained in two wind tunnels for 13 models over a Mach number range from 0.70 to 1.02. Effects of increasing test-section blockage ratio in the transonic region near a Mach number of 1.0 included change in the shape of the drag curves, premature drag creep, delayed drag divergence, and a positive increment of pressures on the model afterbodies. Effects of wall interference were apparent in the data even for a change in blockage ratio from a very low 0.000343 to an even lower 0.000170. Therefore, models having values of blockage ratio of 0.0003 - an order of magnitude below the previously considered safe value of 0.0050 - had significant errors in the drag-coefficient values obtained at speeds near a Mach number of 1.0. Furthermore, the flow relief afforded by slots or perforations in test-section walls - designed according to previously accepted criteria for interference-free subsonic flow - does not appear to be sufficient to avoid significant interference of the walls with the model flow field for Mach numbers very close to 1.0.
Author: George H. Holdaway
Publisher:
Published: 1959
Total Pages: 58
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DOWNLOAD EBOOKAuthor: Michael J. Mann
Publisher:
Published: 1982
Total Pages: 80
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DOWNLOAD EBOOKAuthor: Harry W. Carlson
Publisher:
Published: 1953
Total Pages: 18
ISBN-13:
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