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NACA-RM-L54F25
Effects of canopy, revised vertical tail, and a yaw-damper vane on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01
Year: 1954
Abstract: INTRODUCTION
Various investigations have been conducted that are concerned with the aerodynamic characteristics of the Douglas D-558-II research airplane which is currently undergoing flight tests by the NACA High-Speed Flight Research Station at Edwards Air Force Base, Calif. A 1/16-scale model of the original configuration has been investigated at high subsonic and low supersonic speeds in the Langley 8-foot high-speed tunnel (ref. 1) and at mach number of 1.61 and 2.01 in the Langley 4-by 4-foot supersonic pressure tunnel (refs. 2 and 3). Recently the original model has been modified to simulate more closely the present airplane configuration by the addition of a canopy and by increasing the size of the vertical tail. A small vane simulating that to be used in conjunction with a yaw damping system proposed by the stability Analysis Section of the Langley Aeronautical Laboratory (ref.4) was also incorporated into the model.
The present paper presents the aerodynamic characteristics of the revised model in pitch and sideslip, with and without a yaw-damper vane, at a mach number of 2.01 and a Reynolds number of 1.46 X 10 6 based on the wing mean aerodynamic chord. The model was tested through an angle-of-attack range of about -2° to about 13 at an angel of sideslip of 0° and an angle-of-sideslip range of 2° to about 10 at an angle of attack of 0°. These results are compared with those obtained for the original model configuration.
Various investigations have been conducted that are concerned with the aerodynamic characteristics of the Douglas D-558-II research airplane which is currently undergoing flight tests by the NACA High-Speed Flight Research Station at Edwards Air Force Base, Calif. A 1/16-scale model of the original configuration has been investigated at high subsonic and low supersonic speeds in the Langley 8-foot high-speed tunnel (ref. 1) and at mach number of 1.61 and 2.01 in the Langley 4-by 4-foot supersonic pressure tunnel (refs. 2 and 3). Recently the original model has been modified to simulate more closely the present airplane configuration by the addition of a canopy and by increasing the size of the vertical tail. A small vane simulating that to be used in conjunction with a yaw damping system proposed by the stability Analysis Section of the Langley Aeronautical Laboratory (ref.4) was also incorporated into the model.
The present paper presents the aerodynamic characteristics of the revised model in pitch and sideslip, with and without a yaw-damper vane, at a mach number of 2.01 and a Reynolds number of 1.46 X 10 6 based on the wing mean aerodynamic chord. The model was tested through an angle-of-attack range of about -2° to about 13 at an angel of sideslip of 0° and an angle-of-sideslip range of 2° to about 10 at an angle of attack of 0°. These results are compared with those obtained for the original model configuration.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:44:38Z | |
| date available | 2017-09-04T15:44:38Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | PPSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/47049 | |
| description abstract | INTRODUCTION Various investigations have been conducted that are concerned with the aerodynamic characteristics of the Douglas D-558-II research airplane which is currently undergoing flight tests by the NACA High-Speed Flight Research Station at Edwards Air Force Base, Calif. A 1/16-scale model of the original configuration has been investigated at high subsonic and low supersonic speeds in the Langley 8-foot high-speed tunnel (ref. 1) and at mach number of 1.61 and 2.01 in the Langley 4-by 4-foot supersonic pressure tunnel (refs. 2 and 3). Recently the original model has been modified to simulate more closely the present airplane configuration by the addition of a canopy and by increasing the size of the vertical tail. A small vane simulating that to be used in conjunction with a yaw damping system proposed by the stability Analysis Section of the Langley Aeronautical Laboratory (ref.4) was also incorporated into the model. The present paper presents the aerodynamic characteristics of the revised model in pitch and sideslip, with and without a yaw-damper vane, at a mach number of 2.01 and a Reynolds number of 1.46 X 10 6 based on the wing mean aerodynamic chord. The model was tested through an angle-of-attack range of about -2° to about 13 at an angel of sideslip of 0° and an angle-of-sideslip range of 2° to about 10 at an angle of attack of 0°. These results are compared with those obtained for the original model configuration. | |
| language | English | |
| title | NACA-RM-L54F25 | num |
| title | Effects of canopy, revised vertical tail, and a yaw-damper vane on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01 | en |
| type | standard | |
| page | 31 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |