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NACA-RM-H56H03
Dynamic longitudinal stability characteristics of a swept-wing fighter-type airplane at Mach numbers between 0.36 and 1.45
Year: 1957
Abstract: INTRODUCTION
The static and dynamic longitudinal stability characteristics and derivatives, as determined from flight pulse data, for two wing configurations of a 45° swept-wing fighter-type airplane capable of flight well into the supersonic region are presented in this paper. Stabilizer pulse data employed were obtained for an original-wing configuration and also for a configuration with a 1-foot extension of the wing tip. All data were obtained within the 10,000- and 40,000-foot levels over the Mach number range from 0.36 t o 1.45 at the NACA High-Speed Flight Station at Edwards, Calif.
The results of the flight data analysis are compared with available wind-tunnel data which have been corrected for the momentum effects of the intake air of the jet engine.
This paper constitutes one part of a general flight investigation of the stability, performance, and aerodynamic load characteristics of the airplane. Results of of other investigations have been reported in references 1 to 4.
The static and dynamic longitudinal stability characteristics and derivatives, as determined from flight pulse data, for two wing configurations of a 45° swept-wing fighter-type airplane capable of flight well into the supersonic region are presented in this paper. Stabilizer pulse data employed were obtained for an original-wing configuration and also for a configuration with a 1-foot extension of the wing tip. All data were obtained within the 10,000- and 40,000-foot levels over the Mach number range from 0.36 t o 1.45 at the NACA High-Speed Flight Station at Edwards, Calif.
The results of the flight data analysis are compared with available wind-tunnel data which have been corrected for the momentum effects of the intake air of the jet engine.
This paper constitutes one part of a general flight investigation of the stability, performance, and aerodynamic load characteristics of the airplane. Results of of other investigations have been reported in references 1 to 4.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:18:43Z | |
| date available | 2017-09-04T17:18:43Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | ZLMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/141999 | |
| description abstract | INTRODUCTION The static and dynamic longitudinal stability characteristics and derivatives, as determined from flight pulse data, for two wing configurations of a 45° swept-wing fighter-type airplane capable of flight well into the supersonic region are presented in this paper. Stabilizer pulse data employed were obtained for an original-wing configuration and also for a configuration with a 1-foot extension of the wing tip. All data were obtained within the 10,000- and 40,000-foot levels over the Mach number range from 0.36 t o 1.45 at the NACA High-Speed Flight Station at Edwards, Calif. The results of the flight data analysis are compared with available wind-tunnel data which have been corrected for the momentum effects of the intake air of the jet engine. This paper constitutes one part of a general flight investigation of the stability, performance, and aerodynamic load characteristics of the airplane. Results of of other investigations have been reported in references 1 to 4. | |
| language | English | |
| title | NACA-RM-H56H03 | num |
| title | Dynamic longitudinal stability characteristics of a swept-wing fighter-type airplane at Mach numbers between 0.36 and 1.45 | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |