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NACA-RM-A56B17
Data from large-scale low-speed tests of airplane configurations with a thin 45 degrees swept-wing incorporating several leading-edge contour modifications
Year: 1956
Abstract: INTRODUCTION
The fundamental results of an investigation of the effects of a wing-contour modification designed to improve the low-speed characteristics of a thin swept wing have been reported and analyzed in reference 1. The modification consisted of a greatly increased leading-edge radius and slight forward camber. Data were presented in the report from tests at low sub8onic, high subsonic, and supersonic speeds.
Besides the data reported in reference 1, a considerable amount of additional low-speed data was obtained in the course of the investigation, which was not directly relevant to the basic analysis of reference 1. Specifically, data were obtained on three less extreme wing-contour modifications. Also, for each wing, data were obtained on the effects of horizontal and vertical tails, and on the effects of fences. Some limited data were obtained on the effects of chord extensions, split flaps, and simulated (split-flap-type) ailerons. All testing was done in the Ames 40- by 80-foot wind tunnel.
It is the purpose of this report to present these data. While no analysis is made herein, it is hoped that the report will provide a useful fund of information on a representative interceptor-type configuration. (For the cake of completeness, the low-speed data of ref. 1 are repeated in this report.) It is also hoped that it will provide an indication, when considered in conjunction with the analysis of reference 1, of the possibilities and Limitations of leading-edge contour design for a thin swept wing.
In addition to the high-speed data available in reference 1, additional data obtained at high speeds and/or low Reynolds numbers from tests of wings having the same plan form with various airfoil sections can be found in references 2 through 7. Reference 5 includes data on a wing modification essentially the same as modification 3 of this report. Data on the use of spoilers as lateral controls on the subject model can be found in reference 8.
The fundamental results of an investigation of the effects of a wing-contour modification designed to improve the low-speed characteristics of a thin swept wing have been reported and analyzed in reference 1. The modification consisted of a greatly increased leading-edge radius and slight forward camber. Data were presented in the report from tests at low sub8onic, high subsonic, and supersonic speeds.
Besides the data reported in reference 1, a considerable amount of additional low-speed data was obtained in the course of the investigation, which was not directly relevant to the basic analysis of reference 1. Specifically, data were obtained on three less extreme wing-contour modifications. Also, for each wing, data were obtained on the effects of horizontal and vertical tails, and on the effects of fences. Some limited data were obtained on the effects of chord extensions, split flaps, and simulated (split-flap-type) ailerons. All testing was done in the Ames 40- by 80-foot wind tunnel.
It is the purpose of this report to present these data. While no analysis is made herein, it is hoped that the report will provide a useful fund of information on a representative interceptor-type configuration. (For the cake of completeness, the low-speed data of ref. 1 are repeated in this report.) It is also hoped that it will provide an indication, when considered in conjunction with the analysis of reference 1, of the possibilities and Limitations of leading-edge contour design for a thin swept wing.
In addition to the high-speed data available in reference 1, additional data obtained at high speeds and/or low Reynolds numbers from tests of wings having the same plan form with various airfoil sections can be found in references 2 through 7. Reference 5 includes data on a wing modification essentially the same as modification 3 of this report. Data on the use of spoilers as lateral controls on the subject model can be found in reference 8.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:14:46Z | |
| date available | 2017-09-04T18:14:46Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | HIMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/197715 | |
| description abstract | INTRODUCTION The fundamental results of an investigation of the effects of a wing-contour modification designed to improve the low-speed characteristics of a thin swept wing have been reported and analyzed in reference 1. The modification consisted of a greatly increased leading-edge radius and slight forward camber. Data were presented in the report from tests at low sub8onic, high subsonic, and supersonic speeds. Besides the data reported in reference 1, a considerable amount of additional low-speed data was obtained in the course of the investigation, which was not directly relevant to the basic analysis of reference 1. Specifically, data were obtained on three less extreme wing-contour modifications. Also, for each wing, data were obtained on the effects of horizontal and vertical tails, and on the effects of fences. Some limited data were obtained on the effects of chord extensions, split flaps, and simulated (split-flap-type) ailerons. All testing was done in the Ames 40- by 80-foot wind tunnel. It is the purpose of this report to present these data. While no analysis is made herein, it is hoped that the report will provide a useful fund of information on a representative interceptor-type configuration. (For the cake of completeness, the low-speed data of ref. 1 are repeated in this report.) It is also hoped that it will provide an indication, when considered in conjunction with the analysis of reference 1, of the possibilities and Limitations of leading-edge contour design for a thin swept wing. In addition to the high-speed data available in reference 1, additional data obtained at high speeds and/or low Reynolds numbers from tests of wings having the same plan form with various airfoil sections can be found in references 2 through 7. Reference 5 includes data on a wing modification essentially the same as modification 3 of this report. Data on the use of spoilers as lateral controls on the subject model can be found in reference 8. | |
| language | English | |
| title | NACA-RM-A56B17 | num |
| title | Data from large-scale low-speed tests of airplane configurations with a thin 45 degrees swept-wing incorporating several leading-edge contour modifications | en |
| type | standard | |
| page | 112 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |