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NACA-TN-1813
A study of flow changes associated with airfoil section drag rise at supercritical speeds
Year: 1949
Abstract: A study of experimental pressure distributions and sections was made. A correlation appears to exist between the drag-divergence Mach number and the free-stream Mach number and the free-stream Mach number for which sonic velocity occurs at the airfoil crest, the chordwise station at which the airfoil surface is tangent to the free-stream direction. it was found that, since the Mach number for which sonic velocity occurs at the airfoil crest can be estimated satisfactorily by means of the Prandtl-Glauert rule, a method is provided whereby the drag-divergence Mach number of an airfoil section at a given angle of attack can be estimated from the low-speed pressure distribution and the airfoil profile This method was used to predict with a reasonable degree of accuracy the drag-divergence Mach number of a considerable number of airfoil sections having diverse shapes and a wide range of thickness-chord ratios.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:04:57Z | |
| date available | 2017-09-04T16:04:57Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | RUONEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/68166 | |
| description abstract | A study of experimental pressure distributions and sections was made. A correlation appears to exist between the drag-divergence Mach number and the free-stream Mach number and the free-stream Mach number for which sonic velocity occurs at the airfoil crest, the chordwise station at which the airfoil surface is tangent to the free-stream direction. it was found that, since the Mach number for which sonic velocity occurs at the airfoil crest can be estimated satisfactorily by means of the Prandtl-Glauert rule, a method is provided whereby the drag-divergence Mach number of an airfoil section at a given angle of attack can be estimated from the low-speed pressure distribution and the airfoil profile This method was used to predict with a reasonable degree of accuracy the drag-divergence Mach number of a considerable number of airfoil sections having diverse shapes and a wide range of thickness-chord ratios. | |
| language | English | |
| title | NACA-TN-1813 | num |
| title | A study of flow changes associated with airfoil section drag rise at supercritical speeds | en |
| type | standard | |
| page | 32 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |