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NACA-RM-A8F21
An experimental investigation at large scale of several configurations of an NACA submerged air intake
Year: 1948
Abstract: An investigation of an NACA submerged air intake was conducted on a full--scale model of a fighter—type airplane. This study was made to determine the large—scale aerodynamic characteristics of a submerged air intake proposed as the result of small—scale tests and to compare the pressure-recovery characteristics of the large-and small—scale installations. Additional tests were made to determine the effect.
The data obtained at various angles of attack and inlet—velocity ratios indicated the same favorable characteristics for the inlet that have been noted at small scale. The maximum values of entrance pressure recovery were high (92 percent for the full—scale inlet without deflectors), and the variation of pressure recovery with angle of attack and inlet—velocity ratio was small. Pressure recoveries measured with the full—scale model were approximately 9 percent higher than those measured with the small—scale model. It is shown that differences of boundary—layer thickness could account for 3 percent of this amount.
The data obtained at various angles of attack and inlet—velocity ratios indicated the same favorable characteristics for the inlet that have been noted at small scale. The maximum values of entrance pressure recovery were high (92 percent for the full—scale inlet without deflectors), and the variation of pressure recovery with angle of attack and inlet—velocity ratio was small. Pressure recoveries measured with the full—scale model were approximately 9 percent higher than those measured with the small—scale model. It is shown that differences of boundary—layer thickness could account for 3 percent of this amount.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:53:21Z | |
| date available | 2017-09-04T16:53:21Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | WVITDEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/116741 | |
| description abstract | An investigation of an NACA submerged air intake was conducted on a full--scale model of a fighter—type airplane. This study was made to determine the large—scale aerodynamic characteristics of a submerged air intake proposed as the result of small—scale tests and to compare the pressure-recovery characteristics of the large-and small—scale installations. Additional tests were made to determine the effect. The data obtained at various angles of attack and inlet—velocity ratios indicated the same favorable characteristics for the inlet that have been noted at small scale. The maximum values of entrance pressure recovery were high (92 percent for the full—scale inlet without deflectors), and the variation of pressure recovery with angle of attack and inlet—velocity ratio was small. Pressure recoveries measured with the full—scale model were approximately 9 percent higher than those measured with the small—scale model. It is shown that differences of boundary—layer thickness could account for 3 percent of this amount. | |
| language | English | |
| title | NACA-RM-A8F21 | num |
| title | An experimental investigation at large scale of several configurations of an NACA submerged air intake | en |
| type | standard | |
| page | 60 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |