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NACA-RM-A7J22
High-speed aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and 0 degrees and 45 degrees sweepback
Year: 1948
Abstract: INTRODUCTION
Recently, during recovery of an airplane from a high-speed dive, an unanticipated abrupt pitch-up and a large positive acceleration were encountered. (See reference 1.) In order to determine if the tail characteristics of this airplane were affected by Mach number, tests were made in Ames 16-foot high-speed wind tunnel of a semispan model of the horizontal tail plane of the airplane. The movable surface of the model tail plane is referred to in this report as a flap, for the results are applicable to other control surfaces. The aerodynamic characteristics of this model tail plane were measured with the flap hinge line unswept and swept back 45º.
Recently, during recovery of an airplane from a high-speed dive, an unanticipated abrupt pitch-up and a large positive acceleration were encountered. (See reference 1.) In order to determine if the tail characteristics of this airplane were affected by Mach number, tests were made in Ames 16-foot high-speed wind tunnel of a semispan model of the horizontal tail plane of the airplane. The movable surface of the model tail plane is referred to in this report as a flap, for the results are applicable to other control surfaces. The aerodynamic characteristics of this model tail plane were measured with the flap hinge line unswept and swept back 45º.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:07:06Z | |
| date available | 2017-09-04T18:07:06Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | GOCTUDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/190057 | |
| description abstract | INTRODUCTION Recently, during recovery of an airplane from a high-speed dive, an unanticipated abrupt pitch-up and a large positive acceleration were encountered. (See reference 1.) In order to determine if the tail characteristics of this airplane were affected by Mach number, tests were made in Ames 16-foot high-speed wind tunnel of a semispan model of the horizontal tail plane of the airplane. The movable surface of the model tail plane is referred to in this report as a flap, for the results are applicable to other control surfaces. The aerodynamic characteristics of this model tail plane were measured with the flap hinge line unswept and swept back 45º. | |
| language | English | |
| title | NACA-RM-A7J22 | num |
| title | High-speed aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and 0 degrees and 45 degrees sweepback | en |
| type | standard | |
| page | 88 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |