درباره ما
NACA-RM-L56G12
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
Year: 1956
Abstract: INTRODUCTION
A previous investigation conducted in the Langley 8-foot transonic tunnel (ref. 1) to evaluate some of the effects of a sonic propulsive jet as influenced by changes in afterbody geometry indicated the desirability of studies extending this research to bodies with lower boattail angle and small jet-to-base diameter ratios. The results presented herein are therefore a continuation of the work reported in reference 1 and were obtained in an identical manner. The investigation was conducted at an angle of attack of 0° through the Mach number range from a 0.80 to 1.10, and at each point the jet temperature and –pressure ratio were varied.
Presented in this report are the basic data obtained from the investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbodv design.
A previous investigation conducted in the Langley 8-foot transonic tunnel (ref. 1) to evaluate some of the effects of a sonic propulsive jet as influenced by changes in afterbody geometry indicated the desirability of studies extending this research to bodies with lower boattail angle and small jet-to-base diameter ratios. The results presented herein are therefore a continuation of the work reported in reference 1 and were obtained in an identical manner. The investigation was conducted at an angle of attack of 0° through the Mach number range from a 0.80 to 1.10, and at each point the jet temperature and –pressure ratio were varied.
Presented in this report are the basic data obtained from the investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbodv design.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:07:24Z | |
| date available | 2017-09-04T16:07:24Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | SAYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/70527 | |
| description abstract | INTRODUCTION A previous investigation conducted in the Langley 8-foot transonic tunnel (ref. 1) to evaluate some of the effects of a sonic propulsive jet as influenced by changes in afterbody geometry indicated the desirability of studies extending this research to bodies with lower boattail angle and small jet-to-base diameter ratios. The results presented herein are therefore a continuation of the work reported in reference 1 and were obtained in an identical manner. The investigation was conducted at an angle of attack of 0° through the Mach number range from a 0.80 to 1.10, and at each point the jet temperature and –pressure ratio were varied. Presented in this report are the basic data obtained from the investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbodv design. | |
| language | English | |
| title | NACA-RM-L56G12 | num |
| title | Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies | en |
| type | standard | |
| page | 30 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |