NACA-TR-1051
An analysis of base pressure at supersonic velocities and comparison with experiment
Year: 1951
Abstract: In the first part of the investigation an analysis is made of base pressure in an inviscid fluid, both for two-dimensional and axially symmetric flow. It is shown that for two-dimensional flow, and also for the flow over a body of revolution with a cylindrical sting attached to the base, there are an infinite number of possible solutions satisfying all necessary boundary conditions at any given free-stream Mach number. For the particular case of a body having no sting attached only one solution is possible in an inviscid flow, but it corresponds to zero base drag. Accordingly, it is concluded that a strictly inviscid-fluid theory cannot be satisfactory for practical applications. An approximate semi-empirical analysis for base pressure in a viscous fluid is developed in a second part of the investigation. The semi-empirical analysis is based partly on inviscid-flow calculations.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:29:19Z | |
| date available | 2017-09-04T15:29:19Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | NXDZYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/30518 | |
| description abstract | In the first part of the investigation an analysis is made of base pressure in an inviscid fluid, both for two-dimensional and axially symmetric flow. It is shown that for two-dimensional flow, and also for the flow over a body of revolution with a cylindrical sting attached to the base, there are an infinite number of possible solutions satisfying all necessary boundary conditions at any given free-stream Mach number. For the particular case of a body having no sting attached only one solution is possible in an inviscid flow, but it corresponds to zero base drag. Accordingly, it is concluded that a strictly inviscid-fluid theory cannot be satisfactory for practical applications. An approximate semi-empirical analysis for base pressure in a viscous fluid is developed in a second part of the investigation. The semi-empirical analysis is based partly on inviscid-flow calculations. | |
| language | English | |
| title | NACA-TR-1051 | num |
| title | An analysis of base pressure at supersonic velocities and comparison with experiment | en |
| type | standard | |
| page | 25 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | ANALYSIS | |
| subject keywords | AXISYMMETRIC | |
| subject keywords | BASE | |
| subject keywords | BODIES | |
| subject keywords | BOUNDARY | |
| subject keywords | BOW | |
| subject keywords | COMPARISON | |
| subject keywords | CYLINDRICAL | |
| subject keywords | DRAG | |
| subject keywords | FLOW | |
| subject keywords | FREE | |
| subject keywords | INTERFERENCE | |
| subject keywords | INVISCID | |
| subject keywords | LAMINAR | |
| subject keywords | LAYER | |
| subject keywords | MACH | |
| subject keywords | MATHEMATICS | |
| subject keywords | NUMBER | |
| subject keywords | PRESSURE | |
| subject keywords | PROBLEMS | |
| subject keywords | PROFILES | |
| subject keywords | REVOLUTION | |
| subject keywords | REYNOLDS | |
| subject keywords | SHAPES | |
| subject keywords | SUPERSONIC | |
| subject keywords | SUPPORTS | |
| subject keywords | TESTS | |
| subject keywords | TRANSITION | |
| subject keywords | TUNNEL | |
| subject keywords | TUNNELS | |
| subject keywords | TURBULENT | |
| subject keywords | VALUE | |
| subject keywords | VISCOUS | |
| subject keywords | WAVES | |
| subject keywords | WIND |

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