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NACA-RM-L54G08
Static longitudinal and lateral stability and control characteristics of a model of a 35 degrees swept-wing airplane at a Mach number of 1.41
Year: 1954
Abstract: INTRODUCTION
An investigation of the aerodynamic characteristics of a 35° swept-wing airplane at subsonic, transonic, and low supersonic speeds has been undertaken by the National Advisory Committee for Aeronautics.
This airplane is a jet-propelled day-fighter design having a wing with 35° sweep at the quarter-chord line, an aspect ratio of 4, and a thickness ratio of 6 percent at the root and 4 percent at the tip. The wing is mounted in a semi high position on the fuselage and an all-movable horizontal tail is located slightly below the extended chord line of the wing. The fuselage is indented in the vicinity of the wing in an effort to obtain a desirable area distribution for the purpose of reducing the transonic drag rise.
Tests have been conducted at subsonic speeds in the Langley low turbulence pressure tunnel (unpublished) and through the transonic range in the Langley 8-foot transonic tunnel (unpublished). The present paper contains the results obtained at a mach number of 1.41 in the Langley 4-by 4-foot supersonic pressure tunnel.
An investigation of the aerodynamic characteristics of a 35° swept-wing airplane at subsonic, transonic, and low supersonic speeds has been undertaken by the National Advisory Committee for Aeronautics.
This airplane is a jet-propelled day-fighter design having a wing with 35° sweep at the quarter-chord line, an aspect ratio of 4, and a thickness ratio of 6 percent at the root and 4 percent at the tip. The wing is mounted in a semi high position on the fuselage and an all-movable horizontal tail is located slightly below the extended chord line of the wing. The fuselage is indented in the vicinity of the wing in an effort to obtain a desirable area distribution for the purpose of reducing the transonic drag rise.
Tests have been conducted at subsonic speeds in the Langley low turbulence pressure tunnel (unpublished) and through the transonic range in the Langley 8-foot transonic tunnel (unpublished). The present paper contains the results obtained at a mach number of 1.41 in the Langley 4-by 4-foot supersonic pressure tunnel.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:12:47Z | |
| date available | 2017-09-04T16:12:47Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | SPSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/76033 | |
| description abstract | INTRODUCTION An investigation of the aerodynamic characteristics of a 35° swept-wing airplane at subsonic, transonic, and low supersonic speeds has been undertaken by the National Advisory Committee for Aeronautics. This airplane is a jet-propelled day-fighter design having a wing with 35° sweep at the quarter-chord line, an aspect ratio of 4, and a thickness ratio of 6 percent at the root and 4 percent at the tip. The wing is mounted in a semi high position on the fuselage and an all-movable horizontal tail is located slightly below the extended chord line of the wing. The fuselage is indented in the vicinity of the wing in an effort to obtain a desirable area distribution for the purpose of reducing the transonic drag rise. Tests have been conducted at subsonic speeds in the Langley low turbulence pressure tunnel (unpublished) and through the transonic range in the Langley 8-foot transonic tunnel (unpublished). The present paper contains the results obtained at a mach number of 1.41 in the Langley 4-by 4-foot supersonic pressure tunnel. | |
| language | English | |
| title | NACA-RM-L54G08 | num |
| title | Static longitudinal and lateral stability and control characteristics of a model of a 35 degrees swept-wing airplane at a Mach number of 1.41 | en |
| type | standard | |
| page | 32 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |