درباره ما
NACA-RM-L57C08
An experimental study at high subsonic speeds of several tail configurations on a model having a 45 degrees sweptback wing
Year: 1957
Abstract: INTRODUCTION
The present investigation was made to supplement the study (ref. 1) of tail configurations on a straight-wing model by including additional types of tail configurations on a sweptback-wing model. The primary interest in conducting the present study was to obtain a swept-wing airplane configuration which would retain positive. directional stability throughout the range of angle of attack by use of either conventional or unusual tail arrangements. The configurations investigated included a T-tail, a Y-tail, an H-tail, a W-tail, a +-tail, and a fuselage-mounted conventional tail formed by removing the bottom fin of the +-tail. The effects of fuselage afterbody shape on the aerodynamic characteristics of the model were investigated with some of the tail arrangements by use of a cylindrical fuselage afterbody in addition to the basic tapered afterbody.
Static longitudinal and lateral stability characteristics were determined for the model with the various tail configurations for Mach numbers from 0.60 to 0.94 and for a range of angle of attack up to approximately 25° at the lowest Mach numbers. The wing used in the present tests had an aspect ratio of 4, a taper ratio of 0.30, and a quarter-chord sweep of 45°. All the tails investigated were of rectangular plan form and were unswept.
The present investigation was made to supplement the study (ref. 1) of tail configurations on a straight-wing model by including additional types of tail configurations on a sweptback-wing model. The primary interest in conducting the present study was to obtain a swept-wing airplane configuration which would retain positive. directional stability throughout the range of angle of attack by use of either conventional or unusual tail arrangements. The configurations investigated included a T-tail, a Y-tail, an H-tail, a W-tail, a +-tail, and a fuselage-mounted conventional tail formed by removing the bottom fin of the +-tail. The effects of fuselage afterbody shape on the aerodynamic characteristics of the model were investigated with some of the tail arrangements by use of a cylindrical fuselage afterbody in addition to the basic tapered afterbody.
Static longitudinal and lateral stability characteristics were determined for the model with the various tail configurations for Mach numbers from 0.60 to 0.94 and for a range of angle of attack up to approximately 25° at the lowest Mach numbers. The wing used in the present tests had an aspect ratio of 4, a taper ratio of 0.30, and a quarter-chord sweep of 45°. All the tails investigated were of rectangular plan form and were unswept.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:22:19Z | |
| date available | 2017-09-04T15:22:19Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | NBYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/22436 | |
| description abstract | INTRODUCTION The present investigation was made to supplement the study (ref. 1) of tail configurations on a straight-wing model by including additional types of tail configurations on a sweptback-wing model. The primary interest in conducting the present study was to obtain a swept-wing airplane configuration which would retain positive. directional stability throughout the range of angle of attack by use of either conventional or unusual tail arrangements. The configurations investigated included a T-tail, a Y-tail, an H-tail, a W-tail, a +-tail, and a fuselage-mounted conventional tail formed by removing the bottom fin of the +-tail. The effects of fuselage afterbody shape on the aerodynamic characteristics of the model were investigated with some of the tail arrangements by use of a cylindrical fuselage afterbody in addition to the basic tapered afterbody. Static longitudinal and lateral stability characteristics were determined for the model with the various tail configurations for Mach numbers from 0.60 to 0.94 and for a range of angle of attack up to approximately 25° at the lowest Mach numbers. The wing used in the present tests had an aspect ratio of 4, a taper ratio of 0.30, and a quarter-chord sweep of 45°. All the tails investigated were of rectangular plan form and were unswept. | |
| language | English | |
| title | NACA-RM-L57C08 | num |
| title | An experimental study at high subsonic speeds of several tail configurations on a model having a 45 degrees sweptback wing | en |
| type | standard | |
| page | 55 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |