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NACA-RM-L55J25
Wind-tunnel investigation at high subsonic speeds of some effects of fuselage cross-section shape and wing height on the static longitudinal and lateral stability characteristics of a model having a 45 degrees swept wing
Year: 1956
Abstract: INTRODUCTION
The National Advisory Committee for Aeronautics is conducting wind-tunnel investigations to determine the aerodynamic characteristics of airplane models with various arrangements of the component parts. Some results of investigations at low speed have been reported in1 , reference at high subsonic speeds in reference 2, and at supersonic speeds in references 3 and 4.
This paper presents results which show some effects of fuselage cross-section shape and wing height on the longitudinal aerodynamic characteristics and static lateral derivatives of a model having a 45º swept wing of aspect ratio 4, taper ratio 0 .3, and with an NACA 65A006 airfoil section in combination with a fuselage of fineness ratio 10.95. The test Mach number range was from 0.80 to 0.92; the corresponding Reynolds numbers (based on wing mean aerodynamic chord) varied from2 .5 X 106 to 3.0 x 106 .
The National Advisory Committee for Aeronautics is conducting wind-tunnel investigations to determine the aerodynamic characteristics of airplane models with various arrangements of the component parts. Some results of investigations at low speed have been reported in1 , reference at high subsonic speeds in reference 2, and at supersonic speeds in references 3 and 4.
This paper presents results which show some effects of fuselage cross-section shape and wing height on the longitudinal aerodynamic characteristics and static lateral derivatives of a model having a 45º swept wing of aspect ratio 4, taper ratio 0 .3, and with an NACA 65A006 airfoil section in combination with a fuselage of fineness ratio 10.95. The test Mach number range was from 0.80 to 0.92; the corresponding Reynolds numbers (based on wing mean aerodynamic chord) varied from2 .5 X 106 to 3.0 x 106 .
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:20:40Z | |
| date available | 2017-09-04T17:20:40Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | ZQSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/143837 | |
| description abstract | INTRODUCTION The National Advisory Committee for Aeronautics is conducting wind-tunnel investigations to determine the aerodynamic characteristics of airplane models with various arrangements of the component parts. Some results of investigations at low speed have been reported in1 , reference at high subsonic speeds in reference 2, and at supersonic speeds in references 3 and 4. This paper presents results which show some effects of fuselage cross-section shape and wing height on the longitudinal aerodynamic characteristics and static lateral derivatives of a model having a 45º swept wing of aspect ratio 4, taper ratio 0 .3, and with an NACA 65A006 airfoil section in combination with a fuselage of fineness ratio 10.95. The test Mach number range was from 0.80 to 0.92; the corresponding Reynolds numbers (based on wing mean aerodynamic chord) varied from2 .5 X 106 to 3.0 x 106 . | |
| language | English | |
| title | NACA-RM-L55J25 | num |
| title | Wind-tunnel investigation at high subsonic speeds of some effects of fuselage cross-section shape and wing height on the static longitudinal and lateral stability characteristics of a model having a 45 degrees swept wing | en |
| type | standard | |
| page | 62 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |