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NACA-RM-L52K24
Wind-tunnel investigation to determine the aerodynamic characteristics in steady roll of a model at high subsonic speeds
Year: 1952
Abstract: INTRODUCTION
A general research program is being carried out the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics in pitch, sideslip, and steady-roll of various model configurations. This paper presents data obtained during steady-roll tests of a complete swept-wing model and its component parts. The wing and horizontal tail of the model were swept back 45º at the quarter-chord lines and the vertical tail was swept back 55º at the quarter-chord line. The sting-mounted model was tested through a Mach number range 0.40 to approximately 0.95 which gave a mean test Reynolds number range based on the mean aerodynamic chord of the wing from about 1.8 x 10 6 to approximately 3.0 x 106.
Static longitudinal stability characteristics the wing-fuselage combination of the present model are presented in reference 1.
A general research program is being carried out the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics in pitch, sideslip, and steady-roll of various model configurations. This paper presents data obtained during steady-roll tests of a complete swept-wing model and its component parts. The wing and horizontal tail of the model were swept back 45º at the quarter-chord lines and the vertical tail was swept back 55º at the quarter-chord line. The sting-mounted model was tested through a Mach number range 0.40 to approximately 0.95 which gave a mean test Reynolds number range based on the mean aerodynamic chord of the wing from about 1.8 x 10 6 to approximately 3.0 x 106.
Static longitudinal stability characteristics the wing-fuselage combination of the present model are presented in reference 1.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:16:45Z | |
| date available | 2017-09-04T18:16:45Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | HNSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/199697 | |
| description abstract | INTRODUCTION A general research program is being carried out the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics in pitch, sideslip, and steady-roll of various model configurations. This paper presents data obtained during steady-roll tests of a complete swept-wing model and its component parts. The wing and horizontal tail of the model were swept back 45º at the quarter-chord lines and the vertical tail was swept back 55º at the quarter-chord line. The sting-mounted model was tested through a Mach number range 0.40 to approximately 0.95 which gave a mean test Reynolds number range based on the mean aerodynamic chord of the wing from about 1.8 x 10 6 to approximately 3.0 x 106. Static longitudinal stability characteristics the wing-fuselage combination of the present model are presented in reference 1. | |
| language | English | |
| title | NACA-RM-L52K24 | num |
| title | Wind-tunnel investigation to determine the aerodynamic characteristics in steady roll of a model at high subsonic speeds | en |
| type | standard | |
| page | 40 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |