درباره ما
NACA-TM-1105
Plane and Three-Dimensional Flow at High Subsonic Speeds
Year: 1946
Abstract: For two- and three-dimensional flow in a compressible medium, a simple relation is given by which, to a first approximation, the quantitative influence of compressibility upon the velocities and pressures can be understood in a clear manner. In the application of this relation the distinct behaviors of two-dimensional and axially symmetric three-dimensional flow with increasing Mach number are brought out. For slender elliptic cylinders and ellipsoids of revolution, calculations are made of the critical Mach number; that is, the Mach number at which local sonic velocity is achieved on the body. As a further example, the lifting wing of finite span is considered, and it is shown that the increase of wing lift with Mach number at a given angle of attack is greatly dependent upon the aspect ratio b(exp 2)/F.
Subject: AXISYMMETRIC
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:40:28Z | |
| date available | 2017-09-04T15:40:28Z | |
| date copyright | 01/01/1946 | |
| date issued | 1946 | |
| identifier other | PDYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/42697 | |
| description abstract | For two- and three-dimensional flow in a compressible medium, a simple relation is given by which, to a first approximation, the quantitative influence of compressibility upon the velocities and pressures can be understood in a clear manner. In the application of this relation the distinct behaviors of two-dimensional and axially symmetric three-dimensional flow with increasing Mach number are brought out. For slender elliptic cylinders and ellipsoids of revolution, calculations are made of the critical Mach number; that is, the Mach number at which local sonic velocity is achieved on the body. As a further example, the lifting wing of finite span is considered, and it is shown that the increase of wing lift with Mach number at a given angle of attack is greatly dependent upon the aspect ratio b(exp 2)/F. | |
| language | English | |
| title | NACA-TM-1105 | num |
| title | Plane and Three-Dimensional Flow at High Subsonic Speeds | en |
| type | standard | |
| page | 18 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1946 | |
| contenttype | fulltext | |
| subject keywords | AXISYMMETRIC | |
| subject keywords | BODIES | |
| subject keywords | CRITICAL | |
| subject keywords | CYLINDRICAL | |
| subject keywords | DIMENSIONAL | |
| subject keywords | ELLIPSOIDS | |
| subject keywords | FLOW | |
| subject keywords | MACH | |
| subject keywords | NUMBER | |
| subject keywords | SLENDER | |
| subject keywords | SPEED | |
| subject keywords | SUBSONIC | |
| subject keywords | THREE | |
| subject keywords | TWO | |
| subject keywords | VELOCITY |