درباره ما
NACA-RM-L55G08
Transonic wind-tunnel investigation of effects of windshield shape and canopy location on the aerodynamic characteristics of canopy-body combinations
Year: 1955
Abstract: INTRODUCTION
Recently a wind-tunnel test program was undertaken at the Langley Laboratory of the National Advisory Committee for Aeronautics to obtain aerodynamic data in the transonic and supersonic speed ranges for a series of airplane canopy models mounted on a common fuselage forebody. The primary purpose of this program was to investigate the aerodynamic loads experienced by canopy models that simulate present designs used on high-speed aircraft and to evaluate the effects of such design variables as canopy location, size, and windshield shape.
In the present investigation, both pressure-distribution and force data were obtained in the Langley 8-foot transonic tunnel for four different canopies mounted on a fuselage forebody. Presented in this paper are the six-component force data for the canopy-body configurations as well as the forebody alone. Two of the canopies were mounted well forward on the body and had the same shape behind the windshield but one had a "flat" and the.other a "vee" windshield. The two remaining canopies had a smaller maximum cross-sectional area than the first two and both had flat windshields. The two smaller canopies were located at different longitudinal positions on the body.
The Mach number range for this investigation was from 0.80 to 1.13 while the angle of attack was varied from 0° to 10° and the angle of side-slip was varied from -8° to 8°.
Recently a wind-tunnel test program was undertaken at the Langley Laboratory of the National Advisory Committee for Aeronautics to obtain aerodynamic data in the transonic and supersonic speed ranges for a series of airplane canopy models mounted on a common fuselage forebody. The primary purpose of this program was to investigate the aerodynamic loads experienced by canopy models that simulate present designs used on high-speed aircraft and to evaluate the effects of such design variables as canopy location, size, and windshield shape.
In the present investigation, both pressure-distribution and force data were obtained in the Langley 8-foot transonic tunnel for four different canopies mounted on a fuselage forebody. Presented in this paper are the six-component force data for the canopy-body configurations as well as the forebody alone. Two of the canopies were mounted well forward on the body and had the same shape behind the windshield but one had a "flat" and the.other a "vee" windshield. The two remaining canopies had a smaller maximum cross-sectional area than the first two and both had flat windshields. The two smaller canopies were located at different longitudinal positions on the body.
The Mach number range for this investigation was from 0.80 to 1.13 while the angle of attack was varied from 0° to 10° and the angle of side-slip was varied from -8° to 8°.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:53:54Z | |
| date available | 2017-09-04T15:53:54Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | QQSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/57230 | |
| description abstract | INTRODUCTION Recently a wind-tunnel test program was undertaken at the Langley Laboratory of the National Advisory Committee for Aeronautics to obtain aerodynamic data in the transonic and supersonic speed ranges for a series of airplane canopy models mounted on a common fuselage forebody. The primary purpose of this program was to investigate the aerodynamic loads experienced by canopy models that simulate present designs used on high-speed aircraft and to evaluate the effects of such design variables as canopy location, size, and windshield shape. In the present investigation, both pressure-distribution and force data were obtained in the Langley 8-foot transonic tunnel for four different canopies mounted on a fuselage forebody. Presented in this paper are the six-component force data for the canopy-body configurations as well as the forebody alone. Two of the canopies were mounted well forward on the body and had the same shape behind the windshield but one had a "flat" and the.other a "vee" windshield. The two remaining canopies had a smaller maximum cross-sectional area than the first two and both had flat windshields. The two smaller canopies were located at different longitudinal positions on the body. The Mach number range for this investigation was from 0.80 to 1.13 while the angle of attack was varied from 0° to 10° and the angle of side-slip was varied from -8° to 8°. | |
| language | English | |
| title | NACA-RM-L55G08 | num |
| title | Transonic wind-tunnel investigation of effects of windshield shape and canopy location on the aerodynamic characteristics of canopy-body combinations | en |
| type | standard | |
| page | 56 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |