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NACA-RM-A56I04
The static and dynamic-rotary stability derivatives at subsonic speeds of an airplane model with an unswept wing and a high horizontal tail
Year: 1957
Abstract: INTRODUCTION
A program of research on the dynamic stability derivatives of various airplane models is being carried out in the Ames 12-foot pressure wind tunnel. The models are tested on an apparatus which farces an oscillation with a single degree of freedom. (The apparatus is described in ref. 1.) The results of tests employing this equipment with a triangular-wing model are presented in reference 2.
The present report contains the measured static and dynamic-rotary stability derivatives for a model having an unswept wing of low aspect ratio and a high horizontal tail. These measurements were made to evaluate the separate effects of the model components on each of the derivatives and the relative importance of each derivative on the calculated oscillatory response of a representative airplane. Estimates of the rotary derivatives were made by some of the simpler existing procedures, and the agreement between the theory and experiment is assessed on the basis of the airplane-response calculations.
The static-stability characteristics of a model similar to the model of this report have been reported in reference 3 and 4 for speeds into the supersonic regime. Another similar model has been the subject of a test employing the steady-rolling technique, and the resulting rolling derivatives are presented in reference 5.
A program of research on the dynamic stability derivatives of various airplane models is being carried out in the Ames 12-foot pressure wind tunnel. The models are tested on an apparatus which farces an oscillation with a single degree of freedom. (The apparatus is described in ref. 1.) The results of tests employing this equipment with a triangular-wing model are presented in reference 2.
The present report contains the measured static and dynamic-rotary stability derivatives for a model having an unswept wing of low aspect ratio and a high horizontal tail. These measurements were made to evaluate the separate effects of the model components on each of the derivatives and the relative importance of each derivative on the calculated oscillatory response of a representative airplane. Estimates of the rotary derivatives were made by some of the simpler existing procedures, and the agreement between the theory and experiment is assessed on the basis of the airplane-response calculations.
The static-stability characteristics of a model similar to the model of this report have been reported in reference 3 and 4 for speeds into the supersonic regime. Another similar model has been the subject of a test employing the steady-rolling technique, and the resulting rolling derivatives are presented in reference 5.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:46:03Z | |
| date available | 2017-09-04T18:46:03Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | KIMCWDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/227324 | |
| description abstract | INTRODUCTION A program of research on the dynamic stability derivatives of various airplane models is being carried out in the Ames 12-foot pressure wind tunnel. The models are tested on an apparatus which farces an oscillation with a single degree of freedom. (The apparatus is described in ref. 1.) The results of tests employing this equipment with a triangular-wing model are presented in reference 2. The present report contains the measured static and dynamic-rotary stability derivatives for a model having an unswept wing of low aspect ratio and a high horizontal tail. These measurements were made to evaluate the separate effects of the model components on each of the derivatives and the relative importance of each derivative on the calculated oscillatory response of a representative airplane. Estimates of the rotary derivatives were made by some of the simpler existing procedures, and the agreement between the theory and experiment is assessed on the basis of the airplane-response calculations. The static-stability characteristics of a model similar to the model of this report have been reported in reference 3 and 4 for speeds into the supersonic regime. Another similar model has been the subject of a test employing the steady-rolling technique, and the resulting rolling derivatives are presented in reference 5. | |
| language | English | |
| title | NACA-RM-A56I04 | num |
| title | The static and dynamic-rotary stability derivatives at subsonic speeds of an airplane model with an unswept wing and a high horizontal tail | en |
| type | standard | |
| page | 90 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |