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NACA-RM-A52L16
Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20
Year: 1953
Abstract: INTRODUCTION
The low-speed aerodynamic characteristics of triangular-wing airplane models having wings of aspect ratios. 2, 3, and 4 have been under investigation in the Ames k-O- by &-foot wind tunnel, and results have been reported in references l, 2, and 3: Interest has been expressed in the aerodynamic characteristics of these wings when the plan form was modified by the removal of the pointed tips. As a result of this interest, tests were carried out on the aspect ratios 3 and 4 triangular-wing models with the wing plan forms modified to form trapezoidal wings of-aspect ratio 2 and taper ratios ,of 0.2Q and 0.33, respectively.
Tests were made to ascertain the effectiveness of a high-lift device, two types of lateral controls, and a directional control, using .. control-surface deflections typical of those used in landing. The - horizontal tail was tested in three vertical locations in order to determine the. effect of horizontal-tail vertical location on the longitudinal stability. The wings of both models had slotted, trailing-edge flaps which-were tested both as high lift devices and lateral controls. An all-movable horizontal tail was tested as a longitudinal control on both models, and as-a lateral control on one of the models. A rudder of constant chord was tested as a direct Loan 1 control on one model. The data are presented-without analysis to expedite publication.
The low-speed aerodynamic characteristics of triangular-wing airplane models having wings of aspect ratios. 2, 3, and 4 have been under investigation in the Ames k-O- by &-foot wind tunnel, and results have been reported in references l, 2, and 3: Interest has been expressed in the aerodynamic characteristics of these wings when the plan form was modified by the removal of the pointed tips. As a result of this interest, tests were carried out on the aspect ratios 3 and 4 triangular-wing models with the wing plan forms modified to form trapezoidal wings of-aspect ratio 2 and taper ratios ,of 0.2Q and 0.33, respectively.
Tests were made to ascertain the effectiveness of a high-lift device, two types of lateral controls, and a directional control, using .. control-surface deflections typical of those used in landing. The - horizontal tail was tested in three vertical locations in order to determine the. effect of horizontal-tail vertical location on the longitudinal stability. The wings of both models had slotted, trailing-edge flaps which-were tested both as high lift devices and lateral controls. An all-movable horizontal tail was tested as a longitudinal control on both models, and as-a lateral control on one of the models. A rudder of constant chord was tested as a direct Loan 1 control on one model. The data are presented-without analysis to expedite publication.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:49:57Z | |
| date available | 2017-09-04T15:49:57Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | QFMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/52965 | |
| description abstract | INTRODUCTION The low-speed aerodynamic characteristics of triangular-wing airplane models having wings of aspect ratios. 2, 3, and 4 have been under investigation in the Ames k-O- by &-foot wind tunnel, and results have been reported in references l, 2, and 3: Interest has been expressed in the aerodynamic characteristics of these wings when the plan form was modified by the removal of the pointed tips. As a result of this interest, tests were carried out on the aspect ratios 3 and 4 triangular-wing models with the wing plan forms modified to form trapezoidal wings of-aspect ratio 2 and taper ratios ,of 0.2Q and 0.33, respectively. Tests were made to ascertain the effectiveness of a high-lift device, two types of lateral controls, and a directional control, using .. control-surface deflections typical of those used in landing. The - horizontal tail was tested in three vertical locations in order to determine the. effect of horizontal-tail vertical location on the longitudinal stability. The wings of both models had slotted, trailing-edge flaps which-were tested both as high lift devices and lateral controls. An all-movable horizontal tail was tested as a longitudinal control on both models, and as-a lateral control on one of the models. A rudder of constant chord was tested as a direct Loan 1 control on one model. The data are presented-without analysis to expedite publication. | |
| language | English | |
| title | NACA-RM-A52L16 | num |
| title | Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20 | en |
| type | standard | |
| page | 58 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |