درباره ما
NACA-TN-2941
The drag of finite-length cylinders determined from flight tests at high Reynolds numbers for a Mach number range from 0.5 to 1.3
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:51:45Z | |
| date available | 2017-09-04T16:51:45Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | WRNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/115386 | |
| description abstract | Results of a free-flight investigation to determine the drag of circular, finite-length cylinders are presented for a Mach number range from about 0.5 to 1.3. Also included are drag results of previous experimental tests of infinite-length cylinders. Drag of circular cylinders at supersonic speeds is largely independent of fineness ratio and Reynolds number; whereas, at subsonic speeds, the drag of finite-length cylinders (fineness rations of about 60 and below) increases as their fineness ratios increase. | |
| language | English | |
| title | NACA-TN-2941 | num |
| title | The drag of finite-length cylinders determined from flight tests at high Reynolds numbers for a Mach number range from 0.5 to 1.3 | en |
| type | standard | |
| page | 13 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext | |
| subject keywords | BODIES | |
| subject keywords | FINENESS | |
| subject keywords | RATIO | |
| subject keywords | SHAPE | |
| subject keywords | VARIABLES |
