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NACA-RM-A7K24
Wind-tunnel investigation of horizontal tails. I - unswept and 35 degrees swept-back plan forms of aspect ratio 3
Year: 1948
Abstract: INTRODUCTION
An investigation bf. the theoretical prediction of control surface hinge moments by lifting-surface theory has been undertaken by the NACA. The 1fftIn~UTface theory is a further refinement to the lifting-line theory to obtain more accurate predictions. This report presents the experimental results obtained on the first two. of a series of models to determine the validity of the theoretical computations and the extent of aspect ratios over which they are valid. The comparisons with the theoretical calculations are not presented herein but will await the results of tests of models of aspect ratios 4-5 and 6.
Another equally important purpose of the investigation was to evaluate the effects of sweepback by a comparison of the results of tests of two models with the same area, aspect ratio, taper ratio, and airfoil section, differing mainly in the angle of sweep-back.
The present investigation included the measurement of the lift, hinge-moment, and pitching-moment coefficients, and the pressure coefficients across the elevator nose seal of the semispan horizontal tails of unswept and swept-back plan forms and an aspect ratio of 3. The effects of Reynolds number, standard roughness on the leading edge, and removal of the elevator seal were also determined.
The NACA 64A010 airfoil section was chosen for the models. The aft 30 percent of this section is straight sided, thus simplifying control construction and balance.
An investigation bf. the theoretical prediction of control surface hinge moments by lifting-surface theory has been undertaken by the NACA. The 1fftIn~UTface theory is a further refinement to the lifting-line theory to obtain more accurate predictions. This report presents the experimental results obtained on the first two. of a series of models to determine the validity of the theoretical computations and the extent of aspect ratios over which they are valid. The comparisons with the theoretical calculations are not presented herein but will await the results of tests of models of aspect ratios 4-5 and 6.
Another equally important purpose of the investigation was to evaluate the effects of sweepback by a comparison of the results of tests of two models with the same area, aspect ratio, taper ratio, and airfoil section, differing mainly in the angle of sweep-back.
The present investigation included the measurement of the lift, hinge-moment, and pitching-moment coefficients, and the pressure coefficients across the elevator nose seal of the semispan horizontal tails of unswept and swept-back plan forms and an aspect ratio of 3. The effects of Reynolds number, standard roughness on the leading edge, and removal of the elevator seal were also determined.
The NACA 64A010 airfoil section was chosen for the models. The aft 30 percent of this section is straight sided, thus simplifying control construction and balance.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:17:48Z | |
| date available | 2017-09-04T15:17:48Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | MOCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/17282 | |
| description abstract | INTRODUCTION An investigation bf. the theoretical prediction of control surface hinge moments by lifting-surface theory has been undertaken by the NACA. The 1fftIn~UTface theory is a further refinement to the lifting-line theory to obtain more accurate predictions. This report presents the experimental results obtained on the first two. of a series of models to determine the validity of the theoretical computations and the extent of aspect ratios over which they are valid. The comparisons with the theoretical calculations are not presented herein but will await the results of tests of models of aspect ratios 4-5 and 6. Another equally important purpose of the investigation was to evaluate the effects of sweepback by a comparison of the results of tests of two models with the same area, aspect ratio, taper ratio, and airfoil section, differing mainly in the angle of sweep-back. The present investigation included the measurement of the lift, hinge-moment, and pitching-moment coefficients, and the pressure coefficients across the elevator nose seal of the semispan horizontal tails of unswept and swept-back plan forms and an aspect ratio of 3. The effects of Reynolds number, standard roughness on the leading edge, and removal of the elevator seal were also determined. The NACA 64A010 airfoil section was chosen for the models. The aft 30 percent of this section is straight sided, thus simplifying control construction and balance. | |
| language | English | |
| title | NACA-RM-A7K24 | num |
| title | Wind-tunnel investigation of horizontal tails. I - unswept and 35 degrees swept-back plan forms of aspect ratio 3 | en |
| type | standard | |
| page | 40 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |