درباره ما
NACA-RM-A7L11
Low-speed investigation of a small triangular wing of aspect ratio 2.0 II : flaps on flat-plate models
Year: 1948
Abstract: INTRODUCTION
As a part of a study of the aerodynamic characteristics of a triangular wing of aspect ratio 2.0, the effectiveness of various plain trailing-edge flaps in the transonic speed range has been investigated and reported in reference 1. Further low-speed test results for this wing in combination with constant-chord split flaps have been presented in references 2 and 3.
The 1ow-speed investigation reported herein was made to provide a comparison of the relative effectiveness of split and plain flaps on wings of triangular plan form and further information as to the effects of flap plan form, Included in this investigation was a wing of the same vertex angle and aspect ratio with the plan form modified to include a 45° swept-back, constant-chord, plain flap. For convenience flat-plate models were wed in making the investigation. Some further tests were made using the wing of references with short span split flaps at several chordwise locations.
As a part of a study of the aerodynamic characteristics of a triangular wing of aspect ratio 2.0, the effectiveness of various plain trailing-edge flaps in the transonic speed range has been investigated and reported in reference 1. Further low-speed test results for this wing in combination with constant-chord split flaps have been presented in references 2 and 3.
The 1ow-speed investigation reported herein was made to provide a comparison of the relative effectiveness of split and plain flaps on wings of triangular plan form and further information as to the effects of flap plan form, Included in this investigation was a wing of the same vertex angle and aspect ratio with the plan form modified to include a 45° swept-back, constant-chord, plain flap. For convenience flat-plate models were wed in making the investigation. Some further tests were made using the wing of references with short span split flaps at several chordwise locations.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:41:01Z | |
| date available | 2017-09-04T16:41:01Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | VOCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/104285 | |
| description abstract | INTRODUCTION As a part of a study of the aerodynamic characteristics of a triangular wing of aspect ratio 2.0, the effectiveness of various plain trailing-edge flaps in the transonic speed range has been investigated and reported in reference 1. Further low-speed test results for this wing in combination with constant-chord split flaps have been presented in references 2 and 3. The 1ow-speed investigation reported herein was made to provide a comparison of the relative effectiveness of split and plain flaps on wings of triangular plan form and further information as to the effects of flap plan form, Included in this investigation was a wing of the same vertex angle and aspect ratio with the plan form modified to include a 45° swept-back, constant-chord, plain flap. For convenience flat-plate models were wed in making the investigation. Some further tests were made using the wing of references with short span split flaps at several chordwise locations. | |
| language | English | |
| title | NACA-RM-A7L11 | num |
| title | Low-speed investigation of a small triangular wing of aspect ratio 2.0 II : flaps on flat-plate models | en |
| type | standard | |
| page | 20 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |