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NASA-TN-3391
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
Year: 1955
Abstract: Experimental 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.
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.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:29:06Z | |
| date available | 2017-09-04T15:29:06Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | NWONEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/30294 | |
| description abstract | Experimental 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. | |
| language | English | |
| title | NASA-TN-3391 | num |
| title | 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 | en |
| type | standard | |
| page | 50 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |