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NACA-RM-L50K14
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degrees sweepback force characteristics of the complete configuration and its various components at Mach numbers of 1.40 and 1.59
Year: 1951
Abstract: INTRODUCTION
An investigation has been conducted in the Langley 4- by h-foot supersonic tunnel to determine the aerodynamic characteristics of a relatively large size model of a swept-wing supersonic aircraft configuration. Tests have been conducted on both a force and pressure model of identical configuration at Mach numbers of 1.40 and 1.59 at a Reynolds number of approximately 0.6 x 106 based on wing mean aerodynamic chord. References 1 to 8 present the results of various phases of this investigation. Tests of a small-scale model of the same configuration in the Langley 9-inch.supersonic tunnel are reported in reference 9. An investigation of a rocket-powered model of the same configuration is reported in reference 10.
The present paper deals with the longitudinal- and lateral-force characteristics of the complete aircraft configuration and of various combinations of its components. The data have been analyzed insofar as possible to show the aerodynamic characteristics of each component and the interferences between components. Also included for comparison are some of the integrated pressure results for the wing from reference 3.
The force-model configurations tested were built up by adding to the basic sting-mounted body of revolution in various combinations the canopies, wing, vertical tail, and horizontal tail. The effects of wing-tip skids and stall-control. vanes mounted on the wing were also determined.
An investigation has been conducted in the Langley 4- by h-foot supersonic tunnel to determine the aerodynamic characteristics of a relatively large size model of a swept-wing supersonic aircraft configuration. Tests have been conducted on both a force and pressure model of identical configuration at Mach numbers of 1.40 and 1.59 at a Reynolds number of approximately 0.6 x 106 based on wing mean aerodynamic chord. References 1 to 8 present the results of various phases of this investigation. Tests of a small-scale model of the same configuration in the Langley 9-inch.supersonic tunnel are reported in reference 9. An investigation of a rocket-powered model of the same configuration is reported in reference 10.
The present paper deals with the longitudinal- and lateral-force characteristics of the complete aircraft configuration and of various combinations of its components. The data have been analyzed insofar as possible to show the aerodynamic characteristics of each component and the interferences between components. Also included for comparison are some of the integrated pressure results for the wing from reference 3.
The force-model configurations tested were built up by adding to the basic sting-mounted body of revolution in various combinations the canopies, wing, vertical tail, and horizontal tail. The effects of wing-tip skids and stall-control. vanes mounted on the wing were also determined.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:15:39Z | |
| date available | 2017-09-04T18:15:39Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | HKSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/198523 | |
| description abstract | INTRODUCTION An investigation has been conducted in the Langley 4- by h-foot supersonic tunnel to determine the aerodynamic characteristics of a relatively large size model of a swept-wing supersonic aircraft configuration. Tests have been conducted on both a force and pressure model of identical configuration at Mach numbers of 1.40 and 1.59 at a Reynolds number of approximately 0.6 x 106 based on wing mean aerodynamic chord. References 1 to 8 present the results of various phases of this investigation. Tests of a small-scale model of the same configuration in the Langley 9-inch.supersonic tunnel are reported in reference 9. An investigation of a rocket-powered model of the same configuration is reported in reference 10. The present paper deals with the longitudinal- and lateral-force characteristics of the complete aircraft configuration and of various combinations of its components. The data have been analyzed insofar as possible to show the aerodynamic characteristics of each component and the interferences between components. Also included for comparison are some of the integrated pressure results for the wing from reference 3. The force-model configurations tested were built up by adding to the basic sting-mounted body of revolution in various combinations the canopies, wing, vertical tail, and horizontal tail. The effects of wing-tip skids and stall-control. vanes mounted on the wing were also determined. | |
| language | English | |
| title | NACA-RM-L50K14 | num |
| title | An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degrees sweepback force characteristics of the complete configuration and its various components at Mach numbers of 1.40 and 1.59 | en |
| type | standard | |
| page | 57 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |