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NACA-RM-E54I13
Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers
Year: 1954
Abstract: INTRODUCTION
The advent of sustained supersonic flight has brought renewed interest in the high subsonic speed range as a cruising point for both subsonic and supersonic aircraft. One or the aerodynamic problems in this speed range for which little information is presently available is that of afterbody design. With jet propulsion the problem is complicated by the interference effects of the jet on the flow over the afterbody. In addition, some severe fairing problems are encountered, particularly in the case of an aircraft with jet-engine afterburner inoperative and the b nozzle-exit area reduced to the cruise condition.
The present small-scale investigation was designed to define the severity of the afterbody drag problems and to indicate relatively good design practice for the high subsonic Mach number range. Tests were made at nominal Mach numbers from about 0.6 to 0.9 on conical afterbodies with a convergent nozzle exiting at the base and having various base sizes and boattail angles. Also studied was a series of ejector configurations that simulated some of the afterburner-off conditions that may be encountered in nacelle and fuselage installations.
The advent of sustained supersonic flight has brought renewed interest in the high subsonic speed range as a cruising point for both subsonic and supersonic aircraft. One or the aerodynamic problems in this speed range for which little information is presently available is that of afterbody design. With jet propulsion the problem is complicated by the interference effects of the jet on the flow over the afterbody. In addition, some severe fairing problems are encountered, particularly in the case of an aircraft with jet-engine afterburner inoperative and the b nozzle-exit area reduced to the cruise condition.
The present small-scale investigation was designed to define the severity of the afterbody drag problems and to indicate relatively good design practice for the high subsonic Mach number range. Tests were made at nominal Mach numbers from about 0.6 to 0.9 on conical afterbodies with a convergent nozzle exiting at the base and having various base sizes and boattail angles. Also studied was a series of ejector configurations that simulated some of the afterburner-off conditions that may be encountered in nacelle and fuselage installations.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:55:18Z | |
| date available | 2017-09-04T17:55:18Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | FJMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/178421 | |
| description abstract | INTRODUCTION The advent of sustained supersonic flight has brought renewed interest in the high subsonic speed range as a cruising point for both subsonic and supersonic aircraft. One or the aerodynamic problems in this speed range for which little information is presently available is that of afterbody design. With jet propulsion the problem is complicated by the interference effects of the jet on the flow over the afterbody. In addition, some severe fairing problems are encountered, particularly in the case of an aircraft with jet-engine afterburner inoperative and the b nozzle-exit area reduced to the cruise condition. The present small-scale investigation was designed to define the severity of the afterbody drag problems and to indicate relatively good design practice for the high subsonic Mach number range. Tests were made at nominal Mach numbers from about 0.6 to 0.9 on conical afterbodies with a convergent nozzle exiting at the base and having various base sizes and boattail angles. Also studied was a series of ejector configurations that simulated some of the afterburner-off conditions that may be encountered in nacelle and fuselage installations. | |
| language | English | |
| title | NACA-RM-E54I13 | num |
| title | Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |