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NACA-RM-A8A20
An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane
Year: 1948
Abstract: INTRODUCTION
The early development of NACA submerged air inlets was conducted with the submerged inlets installed in the flat wall of a wind tunnel (references 1 and 2 ). The results of these tests indicated that it should be feasible to design an efficient air-induction system with twin submerged inlets installed on the sides of the fuselage. Placing the submerged inlets on the sides of the fuselage ahead of the jet engine results in a short, straight internal ducting system (references 3 and 4). As the submerged inlets will not protrude outside of the basic fuselage cclntour they should.tend to eliminate, by inertia separation, foreign material (shell cases, rocks, hail, etc.) from the air inducted into the motor.
The results of reference 3 indicate that the relative location of the wing and the submerged inlets might be critical for inlet performance. The purpose of the tests presented in this report was to investigate the effect of the location of the duct inlets on The model was constructed so that, in later tests, their characteristics. Two locations were tested, one forward of the wing where the fuselage boundary layer was thin, and the other farther aft on the fuselage and over the point of maximum thickness of the wing, the effect of a tractor propeller on the ram recovery could be determined
The test results presented in this report were obtained in the Ames 7- by 10-foot wind tunnel No. 2 at the request of the Bureau of Aeronautics, Navy Department.
The early development of NACA submerged air inlets was conducted with the submerged inlets installed in the flat wall of a wind tunnel (references 1 and 2 ). The results of these tests indicated that it should be feasible to design an efficient air-induction system with twin submerged inlets installed on the sides of the fuselage. Placing the submerged inlets on the sides of the fuselage ahead of the jet engine results in a short, straight internal ducting system (references 3 and 4). As the submerged inlets will not protrude outside of the basic fuselage cclntour they should.tend to eliminate, by inertia separation, foreign material (shell cases, rocks, hail, etc.) from the air inducted into the motor.
The results of reference 3 indicate that the relative location of the wing and the submerged inlets might be critical for inlet performance. The purpose of the tests presented in this report was to investigate the effect of the location of the duct inlets on The model was constructed so that, in later tests, their characteristics. Two locations were tested, one forward of the wing where the fuselage boundary layer was thin, and the other farther aft on the fuselage and over the point of maximum thickness of the wing, the effect of a tractor propeller on the ram recovery could be determined
The test results presented in this report were obtained in the Ames 7- by 10-foot wind tunnel No. 2 at the request of the Bureau of Aeronautics, Navy Department.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:30:44Z | |
| date available | 2017-09-04T16:30:44Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | BPCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/94157 | |
| description abstract | INTRODUCTION The early development of NACA submerged air inlets was conducted with the submerged inlets installed in the flat wall of a wind tunnel (references 1 and 2 ). The results of these tests indicated that it should be feasible to design an efficient air-induction system with twin submerged inlets installed on the sides of the fuselage. Placing the submerged inlets on the sides of the fuselage ahead of the jet engine results in a short, straight internal ducting system (references 3 and 4). As the submerged inlets will not protrude outside of the basic fuselage cclntour they should.tend to eliminate, by inertia separation, foreign material (shell cases, rocks, hail, etc.) from the air inducted into the motor. The results of reference 3 indicate that the relative location of the wing and the submerged inlets might be critical for inlet performance. The purpose of the tests presented in this report was to investigate the effect of the location of the duct inlets on The model was constructed so that, in later tests, their characteristics. Two locations were tested, one forward of the wing where the fuselage boundary layer was thin, and the other farther aft on the fuselage and over the point of maximum thickness of the wing, the effect of a tractor propeller on the ram recovery could be determined The test results presented in this report were obtained in the Ames 7- by 10-foot wind tunnel No. 2 at the request of the Bureau of Aeronautics, Navy Department. | |
| language | English | |
| title | NACA-RM-A8A20 | num |
| title | An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane | en |
| type | standard | |
| page | 48 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |