درباره ما
NACA-RM-L7D08
Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70
Year: 1947
Abstract: INTRODUCTION
A full-scale, semispan, horizontal tail surface of a Jet-propelled fighter-type airplane was tested to determine its aerodynamic characteristics at Mach numbers in 'the range of 0.20 and 0.70. The results of force tests and hinge-moment measurements were presented in reference 1. This report presents the results of chordwise and spanwise pressure-distribution measurements.
In the application of wind-tunnel data obtained with solid models of exact profile contour to the calculation of aerodynamic loads on a full-scale airplane wing or tail, it is difficult to allow for the effects of surface distribution. Because surface distortion ordinarily increases with increasing speed and because the effects of a given surface irregularity become magnified at high Mach number, high-speed full-scale tests of actual components of high-speed airplanes are required to determine accurately the aerodynamic characteristics and to investigate the nature of the effects of structural distortion.
The purpose of the present investigation was to supplement the force tests of reference 1 with pressure data which would provide detailed information as to the nature of the flow changes with increasing speed
The tail surface used in this investigation is considered to be typical of present practice as regards structural characteristics, and the results obtained should therefore be generally applicable to the design of tail surfaces for fighter-type airplanes..
A full-scale, semispan, horizontal tail surface of a Jet-propelled fighter-type airplane was tested to determine its aerodynamic characteristics at Mach numbers in 'the range of 0.20 and 0.70. The results of force tests and hinge-moment measurements were presented in reference 1. This report presents the results of chordwise and spanwise pressure-distribution measurements.
In the application of wind-tunnel data obtained with solid models of exact profile contour to the calculation of aerodynamic loads on a full-scale airplane wing or tail, it is difficult to allow for the effects of surface distribution. Because surface distortion ordinarily increases with increasing speed and because the effects of a given surface irregularity become magnified at high Mach number, high-speed full-scale tests of actual components of high-speed airplanes are required to determine accurately the aerodynamic characteristics and to investigate the nature of the effects of structural distortion.
The purpose of the present investigation was to supplement the force tests of reference 1 with pressure data which would provide detailed information as to the nature of the flow changes with increasing speed
The tail surface used in this investigation is considered to be typical of present practice as regards structural characteristics, and the results obtained should therefore be generally applicable to the design of tail surfaces for fighter-type airplanes..
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:08:57Z | |
| date available | 2017-09-04T15:08:57Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | LMMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/6901 | |
| description abstract | INTRODUCTION A full-scale, semispan, horizontal tail surface of a Jet-propelled fighter-type airplane was tested to determine its aerodynamic characteristics at Mach numbers in 'the range of 0.20 and 0.70. The results of force tests and hinge-moment measurements were presented in reference 1. This report presents the results of chordwise and spanwise pressure-distribution measurements. In the application of wind-tunnel data obtained with solid models of exact profile contour to the calculation of aerodynamic loads on a full-scale airplane wing or tail, it is difficult to allow for the effects of surface distribution. Because surface distortion ordinarily increases with increasing speed and because the effects of a given surface irregularity become magnified at high Mach number, high-speed full-scale tests of actual components of high-speed airplanes are required to determine accurately the aerodynamic characteristics and to investigate the nature of the effects of structural distortion. The purpose of the present investigation was to supplement the force tests of reference 1 with pressure data which would provide detailed information as to the nature of the flow changes with increasing speed The tail surface used in this investigation is considered to be typical of present practice as regards structural characteristics, and the results obtained should therefore be generally applicable to the design of tail surfaces for fighter-type airplanes.. | |
| language | English | |
| title | NACA-RM-L7D08 | num |
| title | Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70 | en |
| type | standard | |
| page | 36 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |