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NASA-TN-963
Friction in pipes at supersonic and subsonic velocities
Year: 1945
Abstract: The apparent friction coefficient was determined experimentally for the flow of air through smooth pipes at subsonic and supersonic velocities. Values of the Lach number ranged from 0.27 to 3.87 and of Reynolds number from 1 x 105 to 8.7 x 105. In supersonic flow the results were found to be strongly influenced by the presence of oblique shocks formed at the junction of nozzle and pipe. the effect of these shocks on the coefficient of friction was determined. Nozzle forms were devised which aliminated the shocks and their effects.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:29:46Z | |
| date available | 2017-09-04T18:29:46Z | |
| date copyright | 01/01/1945 | |
| date issued | 1945 | |
| identifier other | IUONEEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;quess=autho1216AF679DDCAC4/handle/yse/212068 | |
| description abstract | The apparent friction coefficient was determined experimentally for the flow of air through smooth pipes at subsonic and supersonic velocities. Values of the Lach number ranged from 0.27 to 3.87 and of Reynolds number from 1 x 105 to 8.7 x 105. In supersonic flow the results were found to be strongly influenced by the presence of oblique shocks formed at the junction of nozzle and pipe. the effect of these shocks on the coefficient of friction was determined. Nozzle forms were devised which aliminated the shocks and their effects. | |
| language | English | |
| title | NASA-TN-963 | num |
| title | Friction in pipes at supersonic and subsonic velocities | en |
| type | standard | |
| page | 42 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1945 | |
| contenttype | fulltext |