درباره ما
NACA-RM-L56D05
Static lateral stability and control characteristics of a model of a 45 degrees swept-wing fighter airplane with various vertical tails at Mach numbers of 1.41, 1.61, and 2.01
Year: 1956
Abstract: INTRODUCTION
A research program has been undertaken in the Langley 4- by 4-foot supersonic tunnel to determine the aerodynamic characteristics of a model of a 45° swept-wing fighter airplane in the mach number range from 1.41 to 2.01. The static longitudinal stability and control characteristics at mach numbers of 1.41, 1.61, and 2.01 are presented in reference 1. Effets of various external stores on the longitudinal and lateral characteristics at mach numbers of 1.61 and 2.01 have been determined but the results are unpublished. Flight-test results of a similar configuration are presented in reference 2.
The present paper contains the static lateral and directional stability and control characteristics at mach numbers of 1.41, 1.61 and 2.01. The Reynolds numbers of the tets based on the wing mean geometric chord varied from 1.40 X 106 to 1.16 X 106. Results were obtained for the model equipped with three different vertical tails of varying area and aspect ratio.
A research program has been undertaken in the Langley 4- by 4-foot supersonic tunnel to determine the aerodynamic characteristics of a model of a 45° swept-wing fighter airplane in the mach number range from 1.41 to 2.01. The static longitudinal stability and control characteristics at mach numbers of 1.41, 1.61, and 2.01 are presented in reference 1. Effets of various external stores on the longitudinal and lateral characteristics at mach numbers of 1.61 and 2.01 have been determined but the results are unpublished. Flight-test results of a similar configuration are presented in reference 2.
The present paper contains the static lateral and directional stability and control characteristics at mach numbers of 1.41, 1.61 and 2.01. The Reynolds numbers of the tets based on the wing mean geometric chord varied from 1.40 X 106 to 1.16 X 106. Results were obtained for the model equipped with three different vertical tails of varying area and aspect ratio.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:01:34Z | |
| date available | 2017-09-04T17:01:34Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | XRSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/125072 | |
| description abstract | INTRODUCTION A research program has been undertaken in the Langley 4- by 4-foot supersonic tunnel to determine the aerodynamic characteristics of a model of a 45° swept-wing fighter airplane in the mach number range from 1.41 to 2.01. The static longitudinal stability and control characteristics at mach numbers of 1.41, 1.61, and 2.01 are presented in reference 1. Effets of various external stores on the longitudinal and lateral characteristics at mach numbers of 1.61 and 2.01 have been determined but the results are unpublished. Flight-test results of a similar configuration are presented in reference 2. The present paper contains the static lateral and directional stability and control characteristics at mach numbers of 1.41, 1.61 and 2.01. The Reynolds numbers of the tets based on the wing mean geometric chord varied from 1.40 X 106 to 1.16 X 106. Results were obtained for the model equipped with three different vertical tails of varying area and aspect ratio. | |
| language | English | |
| title | NACA-RM-L56D05 | num |
| title | Static lateral stability and control characteristics of a model of a 45 degrees swept-wing fighter airplane with various vertical tails at Mach numbers of 1.41, 1.61, and 2.01 | en |
| type | standard | |
| page | 50 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |