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NACA-RM-L52J17
An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration
Year: 1956
Abstract: INTRODUCTION
An investigation of a swept-wing supersonic bomber configuration has been made in the Langley 8-foot transonic tunnel (ref. 1) and the Langley 4- by 4-foot supersonic pressure tunnel This report presents the results of the investigation in the latter tunnel at Mach numbers of 1.41 and 2.01, and a Reynolds number of 2.5 x 106 based on wing mean aerodynamic chord. Longitudinal and lateral force characteristics of the complete aircraft configuration and of various combinations of its components, including several jet nacelle installations, are shown. The effects of a modified wing, a shortened fuselage and two horizontal-tail heights were also studied. Some comparisons of the data with simple theories are presented.
An investigation of a swept-wing supersonic bomber configuration has been made in the Langley 8-foot transonic tunnel (ref. 1) and the Langley 4- by 4-foot supersonic pressure tunnel This report presents the results of the investigation in the latter tunnel at Mach numbers of 1.41 and 2.01, and a Reynolds number of 2.5 x 106 based on wing mean aerodynamic chord. Longitudinal and lateral force characteristics of the complete aircraft configuration and of various combinations of its components, including several jet nacelle installations, are shown. The effects of a modified wing, a shortened fuselage and two horizontal-tail heights were also studied. Some comparisons of the data with simple theories are presented.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:40:02Z | |
| date available | 2017-09-04T16:40:02Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | VMSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/103749 | |
| description abstract | INTRODUCTION An investigation of a swept-wing supersonic bomber configuration has been made in the Langley 8-foot transonic tunnel (ref. 1) and the Langley 4- by 4-foot supersonic pressure tunnel This report presents the results of the investigation in the latter tunnel at Mach numbers of 1.41 and 2.01, and a Reynolds number of 2.5 x 106 based on wing mean aerodynamic chord. Longitudinal and lateral force characteristics of the complete aircraft configuration and of various combinations of its components, including several jet nacelle installations, are shown. The effects of a modified wing, a shortened fuselage and two horizontal-tail heights were also studied. Some comparisons of the data with simple theories are presented. | |
| language | English | |
| title | NACA-RM-L52J17 | num |
| title | An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration | en |
| type | standard | |
| page | 92 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |