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NACA-RM-L53H27
Low-speed static stability and control characteristics of a 1/4-scale model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4, unswept wing
Year: 1953
Abstract: INTRODUCTION
Extensive research as indicated that airfoil thickness is of primary Importance in the performance f aircraft designed to operate the transonic and supersonic speed ranges. At the request of the National Advisory Committee for Aeronautic, a 4percent-thick wing is being incorporated In the Bell X-1 research airplane. The use of thin sections, in general, an accompanying change in aspect ratio or taper ratio, 8 or both from purely structural considerations.
The present paper presents the results of an investigation to determine the effect, if any, that a change in wing thickness and an associated change in aspect ratio would have on the low-speed static stability and control characteristics of the Bell X-1 airplane. The investigation was made in the Langley 300 MPH 7-by 10-foot tunnel with a ¼-scale model of the Bell X-1 airplane equipped with a wing of aspect ratio 4, taper ratio 0.5, 0o sweepback of the 0.40 chord line, and a modified NACA 64A004 airfoil section. The wing had a slotted flap of about 0.50 semispan and an aileron of 0.30 semispan.
Extensive research as indicated that airfoil thickness is of primary Importance in the performance f aircraft designed to operate the transonic and supersonic speed ranges. At the request of the National Advisory Committee for Aeronautic, a 4percent-thick wing is being incorporated In the Bell X-1 research airplane. The use of thin sections, in general, an accompanying change in aspect ratio or taper ratio, 8 or both from purely structural considerations.
The present paper presents the results of an investigation to determine the effect, if any, that a change in wing thickness and an associated change in aspect ratio would have on the low-speed static stability and control characteristics of the Bell X-1 airplane. The investigation was made in the Langley 300 MPH 7-by 10-foot tunnel with a ¼-scale model of the Bell X-1 airplane equipped with a wing of aspect ratio 4, taper ratio 0.5, 0o sweepback of the 0.40 chord line, and a modified NACA 64A004 airfoil section. The wing had a slotted flap of about 0.50 semispan and an aileron of 0.30 semispan.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:02:55Z | |
| date available | 2017-09-04T16:02:55Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | ROSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/66046 | |
| description abstract | INTRODUCTION Extensive research as indicated that airfoil thickness is of primary Importance in the performance f aircraft designed to operate the transonic and supersonic speed ranges. At the request of the National Advisory Committee for Aeronautic, a 4percent-thick wing is being incorporated In the Bell X-1 research airplane. The use of thin sections, in general, an accompanying change in aspect ratio or taper ratio, 8 or both from purely structural considerations. The present paper presents the results of an investigation to determine the effect, if any, that a change in wing thickness and an associated change in aspect ratio would have on the low-speed static stability and control characteristics of the Bell X-1 airplane. The investigation was made in the Langley 300 MPH 7-by 10-foot tunnel with a ¼-scale model of the Bell X-1 airplane equipped with a wing of aspect ratio 4, taper ratio 0.5, 0o sweepback of the 0.40 chord line, and a modified NACA 64A004 airfoil section. The wing had a slotted flap of about 0.50 semispan and an aileron of 0.30 semispan. | |
| language | English | |
| title | NACA-RM-L53H27 | num |
| title | Low-speed static stability and control characteristics of a 1/4-scale model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4, unswept wing | en |
| type | standard | |
| page | 54 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |