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NACA-RM-A52F18
The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10
Year: 1952
Abstract: INTRODUCTION
Military and commercial requirement for higher cruising speeds and altitudes in long-range airplanes have emphasized the need for extending research concerning swept-back wings to include those of large aspect ratio. The design of such wings brings into sharp focus all the conflicting requirements for strength, stiffness, and with weight on the one hand, and for aerodynamic efficiency on the other. Furthermore, the research data available concerning swept-back wings of moderate aspect ratio indicate that a major problem in the aerodynamic design o high aspect ratio wings is likely to be the attainment of satisfactory longitudinal stability characteristics. From a practical viewpoint all these factors must be considered in relation to the airplane performance required.
The present research was undertaken to investigate in the Ames 12-foot pressure wind tunnel a wing and a fuselage satisfying the assumed requirements of long-range, high-speed airplane. The selection of the geometric characteristics of the wing was guided by the results of past experimental research-and by calculations of the aerodynamic characteristics of the wing according to available theoretical methods.
The experimental data presented include lift, drag, and pitching-moment data for the wing alone, the fuselage alone, and the wing-fuselage combination, Included also are data which show the effects of several fence arrangements on the wing, as well as tuft photographs indicating the boundary-layer flow on the upper surface of the wing. The tests covered a range of Mach numbers up to 0.9 at a constant Reynolds number of 2,000,000, and a range of Reynolds numbers up to 8,000,000 at low Mach numbers.
Military and commercial requirement for higher cruising speeds and altitudes in long-range airplanes have emphasized the need for extending research concerning swept-back wings to include those of large aspect ratio. The design of such wings brings into sharp focus all the conflicting requirements for strength, stiffness, and with weight on the one hand, and for aerodynamic efficiency on the other. Furthermore, the research data available concerning swept-back wings of moderate aspect ratio indicate that a major problem in the aerodynamic design o high aspect ratio wings is likely to be the attainment of satisfactory longitudinal stability characteristics. From a practical viewpoint all these factors must be considered in relation to the airplane performance required.
The present research was undertaken to investigate in the Ames 12-foot pressure wind tunnel a wing and a fuselage satisfying the assumed requirements of long-range, high-speed airplane. The selection of the geometric characteristics of the wing was guided by the results of past experimental research-and by calculations of the aerodynamic characteristics of the wing according to available theoretical methods.
The experimental data presented include lift, drag, and pitching-moment data for the wing alone, the fuselage alone, and the wing-fuselage combination, Included also are data which show the effects of several fence arrangements on the wing, as well as tuft photographs indicating the boundary-layer flow on the upper surface of the wing. The tests covered a range of Mach numbers up to 0.9 at a constant Reynolds number of 2,000,000, and a range of Reynolds numbers up to 8,000,000 at low Mach numbers.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:37:03Z | |
| date available | 2017-09-04T16:37:03Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | VEMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/100572 | |
| description abstract | INTRODUCTION Military and commercial requirement for higher cruising speeds and altitudes in long-range airplanes have emphasized the need for extending research concerning swept-back wings to include those of large aspect ratio. The design of such wings brings into sharp focus all the conflicting requirements for strength, stiffness, and with weight on the one hand, and for aerodynamic efficiency on the other. Furthermore, the research data available concerning swept-back wings of moderate aspect ratio indicate that a major problem in the aerodynamic design o high aspect ratio wings is likely to be the attainment of satisfactory longitudinal stability characteristics. From a practical viewpoint all these factors must be considered in relation to the airplane performance required. The present research was undertaken to investigate in the Ames 12-foot pressure wind tunnel a wing and a fuselage satisfying the assumed requirements of long-range, high-speed airplane. The selection of the geometric characteristics of the wing was guided by the results of past experimental research-and by calculations of the aerodynamic characteristics of the wing according to available theoretical methods. The experimental data presented include lift, drag, and pitching-moment data for the wing alone, the fuselage alone, and the wing-fuselage combination, Included also are data which show the effects of several fence arrangements on the wing, as well as tuft photographs indicating the boundary-layer flow on the upper surface of the wing. The tests covered a range of Mach numbers up to 0.9 at a constant Reynolds number of 2,000,000, and a range of Reynolds numbers up to 8,000,000 at low Mach numbers. | |
| language | English | |
| title | NACA-RM-A52F18 | num |
| title | The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10 | en |
| type | standard | |
| page | 73 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |