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Free-flight measurements of turbulent-boundary-layer skin friction in the presence of severe aerodynamic heating at Mach numbers from 2.8 to 7.0

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:29:06Z
date available2017-09-04T15:29:06Z
date copyright01/01/1955
date issued1955
identifier otherNWONEEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/30294
description abstractExperimental measurements of average skin friction of the turbulent boundary layer have been made on free-flying, hollow-cylinder models at Mach numbers of 2.8, 3.8, 5.6, and 7.0, at conditions of high rates of heat transfer. It has been found that for these high theat-transfer conditions, the ratio of skin friction to incompressible skin friction is approximately 35 percent high than zero-heat-transfer wind-tunnel data at Mach numbers of 2.8 and 3.8. Although no measurements of skin friction have been made at zero-heat-transfer conditions at very high Mach numbers, the data of the present investigation indicate that this same trend of increasing skin-friction ratio with increasing heat-transfer rates will persist at Mach numbers as high as 7.
The Rubesin and Johnson T method of calculating skin friction for laminar boundary layers has been modified and compared to the data of this investigation and existing wind-tunnel data for conditions close to zero heat transfer. It has been found that values of skin-friction ratio computed by this method agree well with the experimental values over a wide range of Mach numbers and heat-transfer conditions.
languageEnglish
titleNASA-TN-3391num
titleFree-flight measurements of turbulent-boundary-layer skin friction in the presence of severe aerodynamic heating at Mach numbers from 2.8 to 7.0en
typestandard
page50
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1955
contenttypefulltext


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