درباره ما
NACA-RM-A8I29
Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds
Year: 1948
Abstract: INTRODUCTION
A research program was conducted in the Ames 16-foot high-speed wind tunnel which, in conjunction with work in an Ames 7- by 10-foot wind tunnel, continued the investigation of NACA submerged inlets developed during the tests discussed in references 1 and 2. Attention was concentrated on the inlet design found to have the most satisfactory pressure-recovery characteristics during the tests of reference 1. The effects of the following parameters on the pressure recovery at the inlets were investigated.
1. Aerodynamic parameters
(a) Mach number
(b) Angle of attack
(c) Mass- flow ratio
(d) Boundary-layer thickness
2. Model parameters
(a) Inlet location with respect to wing and fuselage
(b) Inlet lip angle
(c) Boundary-layer deflectors
Data obtained during the present investigation of the model without inlets and with inlets 16.7 percent of the root chord ahead of the wing-root leading edge only was presented extensively in reference 3. To expedite the publication of the pressure-recovery characteristics for the inlets in other configurations, the present report was prepared.
A research program was conducted in the Ames 16-foot high-speed wind tunnel which, in conjunction with work in an Ames 7- by 10-foot wind tunnel, continued the investigation of NACA submerged inlets developed during the tests discussed in references 1 and 2. Attention was concentrated on the inlet design found to have the most satisfactory pressure-recovery characteristics during the tests of reference 1. The effects of the following parameters on the pressure recovery at the inlets were investigated.
1. Aerodynamic parameters
(a) Mach number
(b) Angle of attack
(c) Mass- flow ratio
(d) Boundary-layer thickness
2. Model parameters
(a) Inlet location with respect to wing and fuselage
(b) Inlet lip angle
(c) Boundary-layer deflectors
Data obtained during the present investigation of the model without inlets and with inlets 16.7 percent of the root chord ahead of the wing-root leading edge only was presented extensively in reference 3. To expedite the publication of the pressure-recovery characteristics for the inlets in other configurations, the present report was prepared.
Subject: BODIES
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:28:36Z | |
| date available | 2017-09-04T17:28:36Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | CQCTUDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/151748 | |
| description abstract | INTRODUCTION A research program was conducted in the Ames 16-foot high-speed wind tunnel which, in conjunction with work in an Ames 7- by 10-foot wind tunnel, continued the investigation of NACA submerged inlets developed during the tests discussed in references 1 and 2. Attention was concentrated on the inlet design found to have the most satisfactory pressure-recovery characteristics during the tests of reference 1. The effects of the following parameters on the pressure recovery at the inlets were investigated. 1. Aerodynamic parameters (a) Mach number (b) Angle of attack (c) Mass- flow ratio (d) Boundary-layer thickness 2. Model parameters (a) Inlet location with respect to wing and fuselage (b) Inlet lip angle (c) Boundary-layer deflectors Data obtained during the present investigation of the model without inlets and with inlets 16.7 percent of the root chord ahead of the wing-root leading edge only was presented extensively in reference 3. To expedite the publication of the pressure-recovery characteristics for the inlets in other configurations, the present report was prepared. | |
| language | English | |
| title | NACA-RM-A8I29 | num |
| title | Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds | en |
| type | standard | |
| page | 46 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext | |
| subject keywords | BODIES | |
| subject keywords | DUCTED | |
| subject keywords | INLETS | |
| subject keywords | SIDE | |
| subject keywords | SUBMERGED |