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NACA-RM-L8H12
Yaw characteristics of a 52 degrees sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)
Year: 1948
Abstract: INTRODUCTION
Investigations of the lateral stability of sweepback wings have shown that except at low angels of attack, the lateral-stability parameters are primarily dependent on the stalling characteristics of the wing. The stalling characteristics, in turn, are determined by such factors as the airfoil section employed, the angle of wing sweep, the aspect ratio, the Reynolds number, the high-lift devices used, and the interference effect of other airplane components such as fuselage. A general investigation is being conducted in the Langley 19-foot pressure tunnel to separate the interrelated actions of these various factors and to study their effects on the static lateral stability of swept wings. Previous investigations have been conducted on wings of 420 sweepback and are summarized in references 1 and 2.
The present investigation has been conducted to determine the effects of Reynolds number, leading-edge and split flaps, and a fuselage on the lateral-stability characteristics of a 520 sweptback wing. Air-stream surveys in the region of a vertical tail were also made to ascertain the effects of low aspect ratio and large sweepback angle on the sidewash characteristics. The longitudinal characteristics of the basic wing and the wing with split flaps have been presented in reference 3.
Investigations of the lateral stability of sweepback wings have shown that except at low angels of attack, the lateral-stability parameters are primarily dependent on the stalling characteristics of the wing. The stalling characteristics, in turn, are determined by such factors as the airfoil section employed, the angle of wing sweep, the aspect ratio, the Reynolds number, the high-lift devices used, and the interference effect of other airplane components such as fuselage. A general investigation is being conducted in the Langley 19-foot pressure tunnel to separate the interrelated actions of these various factors and to study their effects on the static lateral stability of swept wings. Previous investigations have been conducted on wings of 420 sweepback and are summarized in references 1 and 2.
The present investigation has been conducted to determine the effects of Reynolds number, leading-edge and split flaps, and a fuselage on the lateral-stability characteristics of a 520 sweptback wing. Air-stream surveys in the region of a vertical tail were also made to ascertain the effects of low aspect ratio and large sweepback angle on the sidewash characteristics. The longitudinal characteristics of the basic wing and the wing with split flaps have been presented in reference 3.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:42:51Z | |
| date available | 2017-09-04T16:42:51Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | VSSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/106115 | |
| description abstract | INTRODUCTION Investigations of the lateral stability of sweepback wings have shown that except at low angels of attack, the lateral-stability parameters are primarily dependent on the stalling characteristics of the wing. The stalling characteristics, in turn, are determined by such factors as the airfoil section employed, the angle of wing sweep, the aspect ratio, the Reynolds number, the high-lift devices used, and the interference effect of other airplane components such as fuselage. A general investigation is being conducted in the Langley 19-foot pressure tunnel to separate the interrelated actions of these various factors and to study their effects on the static lateral stability of swept wings. Previous investigations have been conducted on wings of 420 sweepback and are summarized in references 1 and 2. The present investigation has been conducted to determine the effects of Reynolds number, leading-edge and split flaps, and a fuselage on the lateral-stability characteristics of a 520 sweptback wing. Air-stream surveys in the region of a vertical tail were also made to ascertain the effects of low aspect ratio and large sweepback angle on the sidewash characteristics. The longitudinal characteristics of the basic wing and the wing with split flaps have been presented in reference 3. | |
| language | English | |
| title | NACA-RM-L8H12 | num |
| title | Yaw characteristics of a 52 degrees sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6) | en |
| type | standard | |
| page | 35 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |