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NACA-RM-L56H06
Longitudinal and lateral stability characteristics of a low-aspect-ratio unswept-wing airplane model at Mach numbers of 1.82 and 2.01
Year: 1956
Abstract: INTRODUCTION
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the static longitudinal and lateral stability characteristics of a model of a fighter-type airplane having low-aspect-ratio unswept wings. The complete model and various combinations of its components, including a modified vertical tail and several ventral-fin arrangements, were tested through an angle-of-attack and sideslip range. In addition, the effects of a pylon-mounted fuselage store, two wing-tip-mounted missile configurations, and wing-tip fuel tanks were determined.
The tests were made at Reynolds numbers of 1.38 x 106 and 1.02 x 106 (based on the wing mean geometric chord) for Mach numbers of 1.82 and 2.01, respectively.
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the static longitudinal and lateral stability characteristics of a model of a fighter-type airplane having low-aspect-ratio unswept wings. The complete model and various combinations of its components, including a modified vertical tail and several ventral-fin arrangements, were tested through an angle-of-attack and sideslip range. In addition, the effects of a pylon-mounted fuselage store, two wing-tip-mounted missile configurations, and wing-tip fuel tanks were determined.
The tests were made at Reynolds numbers of 1.38 x 106 and 1.02 x 106 (based on the wing mean geometric chord) for Mach numbers of 1.82 and 2.01, respectively.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:35:46Z | |
| date available | 2017-09-04T16:35:46Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | VAYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/99239 | |
| description abstract | INTRODUCTION An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the static longitudinal and lateral stability characteristics of a model of a fighter-type airplane having low-aspect-ratio unswept wings. The complete model and various combinations of its components, including a modified vertical tail and several ventral-fin arrangements, were tested through an angle-of-attack and sideslip range. In addition, the effects of a pylon-mounted fuselage store, two wing-tip-mounted missile configurations, and wing-tip fuel tanks were determined. The tests were made at Reynolds numbers of 1.38 x 106 and 1.02 x 106 (based on the wing mean geometric chord) for Mach numbers of 1.82 and 2.01, respectively. | |
| language | English | |
| title | NACA-RM-L56H06 | num |
| title | Longitudinal and lateral stability characteristics of a low-aspect-ratio unswept-wing airplane model at Mach numbers of 1.82 and 2.01 | en |
| type | standard | |
| page | 71 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |