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NACA-RM-L52A29
Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds aspect-ratio series
Year: 1952
Abstract: INTRODUCTION
A systematic research program is being carried out in the Langley high-speed 7-by 10-foot wind tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Results are being obtained on characteristics in pitch, yaw, and during steady rolling up to a Mach number of about 0.95. The models are mounted on a sting-type support system. Reynolds numbers range between 1,500,000 and 6,000,000, depending on the wing plan forms and test Mach numbers.
The wing plan forms are similar, in general, to the plan forms investigated at lower Reynolds numbers during a previous research program which utilized the transonic-bump technique for obtaining results at transonic speeds. Some of the results obtained from the transonic-bump program have been summarized in reference 1. Some higher-scale tests of similar or related wing plan forms have been performed in other wind tunnels (references 2 to 4). A comparison of aerodynamic characteristics in pitch as obtained by different test techniques has been reported in reference 5.
The present paper presents results which show the effect of aspect ratio on the pitch characteristics of wings having a sweep angle of 45°, a taper ratio of 0.6, and an NACA 65A006 airfoil section in combination with a fuselage. In order to expedite the issuance of the results, only a limited analysis has been made, although comparisons of some of the more significant characteristics with available theory are presented.
A systematic research program is being carried out in the Langley high-speed 7-by 10-foot wind tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Results are being obtained on characteristics in pitch, yaw, and during steady rolling up to a Mach number of about 0.95. The models are mounted on a sting-type support system. Reynolds numbers range between 1,500,000 and 6,000,000, depending on the wing plan forms and test Mach numbers.
The wing plan forms are similar, in general, to the plan forms investigated at lower Reynolds numbers during a previous research program which utilized the transonic-bump technique for obtaining results at transonic speeds. Some of the results obtained from the transonic-bump program have been summarized in reference 1. Some higher-scale tests of similar or related wing plan forms have been performed in other wind tunnels (references 2 to 4). A comparison of aerodynamic characteristics in pitch as obtained by different test techniques has been reported in reference 5.
The present paper presents results which show the effect of aspect ratio on the pitch characteristics of wings having a sweep angle of 45°, a taper ratio of 0.6, and an NACA 65A006 airfoil section in combination with a fuselage. In order to expedite the issuance of the results, only a limited analysis has been made, although comparisons of some of the more significant characteristics with available theory are presented.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:59:22Z | |
| date available | 2017-09-04T16:59:22Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | XLSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/122803 | |
| description abstract | INTRODUCTION A systematic research program is being carried out in the Langley high-speed 7-by 10-foot wind tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Results are being obtained on characteristics in pitch, yaw, and during steady rolling up to a Mach number of about 0.95. The models are mounted on a sting-type support system. Reynolds numbers range between 1,500,000 and 6,000,000, depending on the wing plan forms and test Mach numbers. The wing plan forms are similar, in general, to the plan forms investigated at lower Reynolds numbers during a previous research program which utilized the transonic-bump technique for obtaining results at transonic speeds. Some of the results obtained from the transonic-bump program have been summarized in reference 1. Some higher-scale tests of similar or related wing plan forms have been performed in other wind tunnels (references 2 to 4). A comparison of aerodynamic characteristics in pitch as obtained by different test techniques has been reported in reference 5. The present paper presents results which show the effect of aspect ratio on the pitch characteristics of wings having a sweep angle of 45°, a taper ratio of 0.6, and an NACA 65A006 airfoil section in combination with a fuselage. In order to expedite the issuance of the results, only a limited analysis has been made, although comparisons of some of the more significant characteristics with available theory are presented. | |
| language | English | |
| title | NACA-RM-L52A29 | num |
| title | Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds aspect-ratio series | en |
| type | standard | |
| page | 43 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |