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NACA-TN-2960
Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers
Year: 1953
Abstract: Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented.
Drag data are presented for the Mach number range of 0.3 to 2.9. The Reynolds numbers for the subsonic and supersonic Mach numbers were within the ranges of approximately 50,000 to 160,000 and 100,000 to 1,000,000, respectively. No effects of Reynolds number were found for flow in the supersonic Mach number to a maximum of approximately 2.1 at a Mach number of unity. In the supersonic Mach number range, the drag coefficient decreased with increasing Mach number to a value of about 1.34 at a Mach number of 2.9. Drag data from other investigations have been included for comparison.
Drag data are presented for the Mach number range of 0.3 to 2.9. The Reynolds numbers for the subsonic and supersonic Mach numbers were within the ranges of approximately 50,000 to 160,000 and 100,000 to 1,000,000, respectively. No effects of Reynolds number were found for flow in the supersonic Mach number to a maximum of approximately 2.1 at a Mach number of unity. In the supersonic Mach number range, the drag coefficient decreased with increasing Mach number to a value of about 1.34 at a Mach number of 2.9. Drag data from other investigations have been included for comparison.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:58:48Z | |
| date available | 2017-09-04T17:58:48Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | FSNUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/181943 | |
| description abstract | Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9. The Reynolds numbers for the subsonic and supersonic Mach numbers were within the ranges of approximately 50,000 to 160,000 and 100,000 to 1,000,000, respectively. No effects of Reynolds number were found for flow in the supersonic Mach number to a maximum of approximately 2.1 at a Mach number of unity. In the supersonic Mach number range, the drag coefficient decreased with increasing Mach number to a value of about 1.34 at a Mach number of 2.9. Drag data from other investigations have been included for comparison. | |
| language | English | |
| title | NACA-TN-2960 | num |
| title | Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers | en |
| type | standard | |
| page | 27 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |