درباره ما
NACA-RM-L51C30
Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions
Year: 1951
Abstract: INTRODUCTION
As part of a general study at the Langley 19-foot pressure tunnel to determine the effect a horizontal tail on the longitudinal stability characteristics of swept wings, a low-speed investigation has been made oaf 52° sweptback wing in combination with a fuselage and a horizontal tail. The wing had symmetrical circular-arc sections, an aspect ratio of 2.84, and a taper ratio of 0.616. The longitudinal characteristics of the wing alone, with and without leading-edge and trailing-edge flaps, are presented in reference 1.
This paper presents results which show the effects of a fuselage and a horizontal tail (at various vertical positions) on the longitudinal characteristics of the wing with and without leading-edge and trailing-edge flaps. Results are also included of air-flow surveys made behind the wing at a longitudinal location which corresponded approximately to the longitudinal location of the tail.
The data presented herein were obtained Reynolds number of 5.5 x 106 and a Mach number of 0.11.
As part of a general study at the Langley 19-foot pressure tunnel to determine the effect a horizontal tail on the longitudinal stability characteristics of swept wings, a low-speed investigation has been made oaf 52° sweptback wing in combination with a fuselage and a horizontal tail. The wing had symmetrical circular-arc sections, an aspect ratio of 2.84, and a taper ratio of 0.616. The longitudinal characteristics of the wing alone, with and without leading-edge and trailing-edge flaps, are presented in reference 1.
This paper presents results which show the effects of a fuselage and a horizontal tail (at various vertical positions) on the longitudinal characteristics of the wing with and without leading-edge and trailing-edge flaps. Results are also included of air-flow surveys made behind the wing at a longitudinal location which corresponded approximately to the longitudinal location of the tail.
The data presented herein were obtained Reynolds number of 5.5 x 106 and a Mach number of 0.11.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:18:21Z | |
| date available | 2017-09-04T17:18:21Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | ZKSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/141715 | |
| description abstract | INTRODUCTION As part of a general study at the Langley 19-foot pressure tunnel to determine the effect a horizontal tail on the longitudinal stability characteristics of swept wings, a low-speed investigation has been made oaf 52° sweptback wing in combination with a fuselage and a horizontal tail. The wing had symmetrical circular-arc sections, an aspect ratio of 2.84, and a taper ratio of 0.616. The longitudinal characteristics of the wing alone, with and without leading-edge and trailing-edge flaps, are presented in reference 1. This paper presents results which show the effects of a fuselage and a horizontal tail (at various vertical positions) on the longitudinal characteristics of the wing with and without leading-edge and trailing-edge flaps. Results are also included of air-flow surveys made behind the wing at a longitudinal location which corresponded approximately to the longitudinal location of the tail. The data presented herein were obtained Reynolds number of 5.5 x 106 and a Mach number of 0.11. | |
| language | English | |
| title | NACA-RM-L51C30 | num |
| title | Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions | en |
| type | standard | |
| page | 46 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |