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NACA-RM-L54I20
Experimental investigation at high subsonic speeds of the rolling stability derivatives of a complete model with an aspect-ratio-2.52 wing having an unswept 72-percent-chord line and a high horizontal tail
Year: 1954
Abstract: INTRODUCTION
A series of tests were made in the Langley high-speed 7- by 10-foot tunnel to determine the rolling stability derivatives of a complete model having a low-aspect-ratio wing and tail. The model had a wing of aspect ratio 2.52, a taper ratio of 0.385, and zero sweep of the 72-percent chord line (19.1° sweepback of the quarter-chord line). The wing airfoil was a modified biconvex section of 3.4-percent-chord thickness having an elliptical nose profile.
Results are presented for the basic configuration over a Mach number range from 0.70 to 0.94 and for a maximum angle-of-attack range of approximate 0° to 13°. A number of breakdown tests were made to determine the contribution of the tail surfaces to the rolling derivatives of the model with and without the wing. Tests also were made to obtain the effects of wing-tip tanks with ailerons undeflected and deflected. A few tests were made with 92.5-percent-span leading-edge flaps deflected.
Analysis and discussion of the test results have been made brief in order t o expedite publication of these data.
A series of tests were made in the Langley high-speed 7- by 10-foot tunnel to determine the rolling stability derivatives of a complete model having a low-aspect-ratio wing and tail. The model had a wing of aspect ratio 2.52, a taper ratio of 0.385, and zero sweep of the 72-percent chord line (19.1° sweepback of the quarter-chord line). The wing airfoil was a modified biconvex section of 3.4-percent-chord thickness having an elliptical nose profile.
Results are presented for the basic configuration over a Mach number range from 0.70 to 0.94 and for a maximum angle-of-attack range of approximate 0° to 13°. A number of breakdown tests were made to determine the contribution of the tail surfaces to the rolling derivatives of the model with and without the wing. Tests also were made to obtain the effects of wing-tip tanks with ailerons undeflected and deflected. A few tests were made with 92.5-percent-span leading-edge flaps deflected.
Analysis and discussion of the test results have been made brief in order t o expedite publication of these data.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:36:37Z | |
| date available | 2017-09-04T16:36:37Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | BQSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/100167 | |
| description abstract | INTRODUCTION A series of tests were made in the Langley high-speed 7- by 10-foot tunnel to determine the rolling stability derivatives of a complete model having a low-aspect-ratio wing and tail. The model had a wing of aspect ratio 2.52, a taper ratio of 0.385, and zero sweep of the 72-percent chord line (19.1° sweepback of the quarter-chord line). The wing airfoil was a modified biconvex section of 3.4-percent-chord thickness having an elliptical nose profile. Results are presented for the basic configuration over a Mach number range from 0.70 to 0.94 and for a maximum angle-of-attack range of approximate 0° to 13°. A number of breakdown tests were made to determine the contribution of the tail surfaces to the rolling derivatives of the model with and without the wing. Tests also were made to obtain the effects of wing-tip tanks with ailerons undeflected and deflected. A few tests were made with 92.5-percent-span leading-edge flaps deflected. Analysis and discussion of the test results have been made brief in order t o expedite publication of these data. | |
| language | English | |
| title | NACA-RM-L54I20 | num |
| title | Experimental investigation at high subsonic speeds of the rolling stability derivatives of a complete model with an aspect-ratio-2.52 wing having an unswept 72-percent-chord line and a high horizontal tail | en |
| type | standard | |
| page | 43 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |