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NACA-RM-A50C13
Preliminary investigation of the transonic characteristics of an NACA submerged inlet
Year: 1950
Abstract: INTRODUCTION
The location of air inlets on the sides of the fuselages of jet-propelled aircraft has received special emphasis recently because of the necessity of housing radar and armament in the fuselage noses, Although a side location generally introduce boundary-layer problems, a distinct advantage is gained by the shorter internal ducting from the air inlet to the compressor. As a result of wind-tunnel tests directed toward the development of a side inlet having high pressure-recovery characteristics and minimum adverse effects from the fuselage boundary layer, the NACA submerged inlet was conceived. Several variations of this inlet were investigated in one of the Ames 7- by 10-foot wind tunnels and are discussed in reference 1. A design judged from the results of those tests to be optimum was then tested on a wing-body combination in the Ames 16-foot high-speed wind tunnel up to a free-steam Mach number of 0.875. This free-steam Mach number corresponded to slightly higher local Mach numbers at the inlet, depending upon the location of the inlet with respect to the wing and fuselage. (See reference 2.) The preliminary investigation reported herein was conducted using an identical inlet mounted on an almost flat, two-dimensional surface of a transonic bump in the Ames 16-foot high-speed wind tunnel. For these tests the local Mach number over the bump in the region of the inlet ranged from 0.70 to 1.15.
The location of air inlets on the sides of the fuselages of jet-propelled aircraft has received special emphasis recently because of the necessity of housing radar and armament in the fuselage noses, Although a side location generally introduce boundary-layer problems, a distinct advantage is gained by the shorter internal ducting from the air inlet to the compressor. As a result of wind-tunnel tests directed toward the development of a side inlet having high pressure-recovery characteristics and minimum adverse effects from the fuselage boundary layer, the NACA submerged inlet was conceived. Several variations of this inlet were investigated in one of the Ames 7- by 10-foot wind tunnels and are discussed in reference 1. A design judged from the results of those tests to be optimum was then tested on a wing-body combination in the Ames 16-foot high-speed wind tunnel up to a free-steam Mach number of 0.875. This free-steam Mach number corresponded to slightly higher local Mach numbers at the inlet, depending upon the location of the inlet with respect to the wing and fuselage. (See reference 2.) The preliminary investigation reported herein was conducted using an identical inlet mounted on an almost flat, two-dimensional surface of a transonic bump in the Ames 16-foot high-speed wind tunnel. For these tests the local Mach number over the bump in the region of the inlet ranged from 0.70 to 1.15.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:41:48Z | |
| date available | 2017-09-04T16:41:48Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | BSCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/105157 | |
| description abstract | INTRODUCTION The location of air inlets on the sides of the fuselages of jet-propelled aircraft has received special emphasis recently because of the necessity of housing radar and armament in the fuselage noses, Although a side location generally introduce boundary-layer problems, a distinct advantage is gained by the shorter internal ducting from the air inlet to the compressor. As a result of wind-tunnel tests directed toward the development of a side inlet having high pressure-recovery characteristics and minimum adverse effects from the fuselage boundary layer, the NACA submerged inlet was conceived. Several variations of this inlet were investigated in one of the Ames 7- by 10-foot wind tunnels and are discussed in reference 1. A design judged from the results of those tests to be optimum was then tested on a wing-body combination in the Ames 16-foot high-speed wind tunnel up to a free-steam Mach number of 0.875. This free-steam Mach number corresponded to slightly higher local Mach numbers at the inlet, depending upon the location of the inlet with respect to the wing and fuselage. (See reference 2.) The preliminary investigation reported herein was conducted using an identical inlet mounted on an almost flat, two-dimensional surface of a transonic bump in the Ames 16-foot high-speed wind tunnel. For these tests the local Mach number over the bump in the region of the inlet ranged from 0.70 to 1.15. | |
| language | English | |
| title | NACA-RM-A50C13 | num |
| title | Preliminary investigation of the transonic characteristics of an NACA submerged inlet | en |
| type | standard | |
| page | 47 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |