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NACA-RM-A50E02
Pressure-distribution and ram-recovery characteristics of NACA submerged inlets at high subsonic speeds
Year: 1950
Abstract: INTRODUCTION
Test were conducted in the Ames 16-foot high-speed wind tunnel to continue investigation, at higher subsonic Mach numbers, of NACA submerged inlets developed in the Ames 7- by 10-foot wing tunnels as discussed in references 1 and 2. For the tests in the 16-foot wind tunnel, the inlets were mounted at four longitudinal locations on a model of a hypothetical fighter airplane. Results of tests in the 16-foot wind tunnel for inlets in the most forward position on the fuselage and with boundary-layer deflectors were reported in reference 3 with the presentation of ram-recovery ratios, mass-flow ratios, and pressure distribution. Results for inlets at four positions on the fuselage (with and without boundary-layer deflectors) were reported in reference 4 with the presentation of ram-recovery ratios and mass-flow ratios. To expedite release, reference 4 presented ram-recovery and mass-flow ratios computed from pressure data averaged during the tests by an integrating manometer. The present report presents ram-recovery and mass-flow ratios computed from the data used in reference 4, but computed by the method of reference 3, which yields more precise values of pressure recovery and local mass-flow ratios in the inlet mounted in the rearmost position are also presented.
Test were conducted in the Ames 16-foot high-speed wind tunnel to continue investigation, at higher subsonic Mach numbers, of NACA submerged inlets developed in the Ames 7- by 10-foot wing tunnels as discussed in references 1 and 2. For the tests in the 16-foot wind tunnel, the inlets were mounted at four longitudinal locations on a model of a hypothetical fighter airplane. Results of tests in the 16-foot wind tunnel for inlets in the most forward position on the fuselage and with boundary-layer deflectors were reported in reference 3 with the presentation of ram-recovery ratios, mass-flow ratios, and pressure distribution. Results for inlets at four positions on the fuselage (with and without boundary-layer deflectors) were reported in reference 4 with the presentation of ram-recovery ratios and mass-flow ratios. To expedite release, reference 4 presented ram-recovery and mass-flow ratios computed from pressure data averaged during the tests by an integrating manometer. The present report presents ram-recovery and mass-flow ratios computed from the data used in reference 4, but computed by the method of reference 3, which yields more precise values of pressure recovery and local mass-flow ratios in the inlet mounted in the rearmost position are also presented.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:39:04Z | |
| date available | 2017-09-04T18:39:04Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | JRCTUDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=authoCA5893FD081D49A96159DD6EFDEC014A/handle/yse/220721 | |
| description abstract | INTRODUCTION Test were conducted in the Ames 16-foot high-speed wind tunnel to continue investigation, at higher subsonic Mach numbers, of NACA submerged inlets developed in the Ames 7- by 10-foot wing tunnels as discussed in references 1 and 2. For the tests in the 16-foot wind tunnel, the inlets were mounted at four longitudinal locations on a model of a hypothetical fighter airplane. Results of tests in the 16-foot wind tunnel for inlets in the most forward position on the fuselage and with boundary-layer deflectors were reported in reference 3 with the presentation of ram-recovery ratios, mass-flow ratios, and pressure distribution. Results for inlets at four positions on the fuselage (with and without boundary-layer deflectors) were reported in reference 4 with the presentation of ram-recovery ratios and mass-flow ratios. To expedite release, reference 4 presented ram-recovery and mass-flow ratios computed from pressure data averaged during the tests by an integrating manometer. The present report presents ram-recovery and mass-flow ratios computed from the data used in reference 4, but computed by the method of reference 3, which yields more precise values of pressure recovery and local mass-flow ratios in the inlet mounted in the rearmost position are also presented. | |
| language | English | |
| title | NACA-RM-A50E02 | num |
| title | Pressure-distribution and ram-recovery characteristics of NACA submerged inlets at high subsonic speeds | en |
| type | standard | |
| page | 42 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |