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NACA-RM-L55K11
Experimental investigation at high subsonic speed of the rolling stability derivatives of a complete model having a clipped-delta wing and a high horizontal tail
Year: 1956
Abstract: INTRODUCTION
Wind-tunnel results at high subsonic speeds pertaining to rolling-stability derivatives for lifting conditions have been obtained for a fairly wide range of wing plan forms (refs. 1 to 3). These derivatives were obtained on model configurations without tail surfaces and more experimental data have been needed to indicate the applicability of existing procedures based on low-speed results for estimating the tail contribution to rolling-stability derivatives. The present test results were obtained as part of a research program to determine the longitudinal, lateral, and rolling-stability characteristics of a general research model. Results presenting the static longitudinal stability of the model are given in reference 4. The clipped-delta wing of the model was of aspect ratio 3, taper ratio 0.143, and had NACA 65A006 airfoil sections. The leading edge of the wing and of the delta plan-form horizontal tail were swept back 45° and the horizontal tail was located at the tip of a swept vertical tail approximately 65-percent wing semispan above the wing chord plane. The model was tested in the Langley high-speed 7-by 10-foot tunnel over a Mach number range from 0.60 to 0.92 and an angle-of-attack range from 0° to a maximum of approximately 13°.
In addition to tests of the complete model, breakdown tests were made in order to determine the contribution of the tail surfaces to the rolling derivatives of the model with and without the wing. Test results for other models having both swept and unswept wings, which show contributions of the model components in addition to the complete model rolling derivatives, are presented in references 5 and 6.
Wind-tunnel results at high subsonic speeds pertaining to rolling-stability derivatives for lifting conditions have been obtained for a fairly wide range of wing plan forms (refs. 1 to 3). These derivatives were obtained on model configurations without tail surfaces and more experimental data have been needed to indicate the applicability of existing procedures based on low-speed results for estimating the tail contribution to rolling-stability derivatives. The present test results were obtained as part of a research program to determine the longitudinal, lateral, and rolling-stability characteristics of a general research model. Results presenting the static longitudinal stability of the model are given in reference 4. The clipped-delta wing of the model was of aspect ratio 3, taper ratio 0.143, and had NACA 65A006 airfoil sections. The leading edge of the wing and of the delta plan-form horizontal tail were swept back 45° and the horizontal tail was located at the tip of a swept vertical tail approximately 65-percent wing semispan above the wing chord plane. The model was tested in the Langley high-speed 7-by 10-foot tunnel over a Mach number range from 0.60 to 0.92 and an angle-of-attack range from 0° to a maximum of approximately 13°.
In addition to tests of the complete model, breakdown tests were made in order to determine the contribution of the tail surfaces to the rolling derivatives of the model with and without the wing. Test results for other models having both swept and unswept wings, which show contributions of the model components in addition to the complete model rolling derivatives, are presented in references 5 and 6.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:29:16Z | |
| date available | 2017-09-04T17:29:16Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | CRSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/152320 | |
| description abstract | INTRODUCTION Wind-tunnel results at high subsonic speeds pertaining to rolling-stability derivatives for lifting conditions have been obtained for a fairly wide range of wing plan forms (refs. 1 to 3). These derivatives were obtained on model configurations without tail surfaces and more experimental data have been needed to indicate the applicability of existing procedures based on low-speed results for estimating the tail contribution to rolling-stability derivatives. The present test results were obtained as part of a research program to determine the longitudinal, lateral, and rolling-stability characteristics of a general research model. Results presenting the static longitudinal stability of the model are given in reference 4. The clipped-delta wing of the model was of aspect ratio 3, taper ratio 0.143, and had NACA 65A006 airfoil sections. The leading edge of the wing and of the delta plan-form horizontal tail were swept back 45° and the horizontal tail was located at the tip of a swept vertical tail approximately 65-percent wing semispan above the wing chord plane. The model was tested in the Langley high-speed 7-by 10-foot tunnel over a Mach number range from 0.60 to 0.92 and an angle-of-attack range from 0° to a maximum of approximately 13°. In addition to tests of the complete model, breakdown tests were made in order to determine the contribution of the tail surfaces to the rolling derivatives of the model with and without the wing. Test results for other models having both swept and unswept wings, which show contributions of the model components in addition to the complete model rolling derivatives, are presented in references 5 and 6. | |
| language | English | |
| title | NACA-RM-L55K11 | num |
| title | Experimental investigation at high subsonic speed of the rolling stability derivatives of a complete model having a clipped-delta wing and a high horizontal tail | en |
| type | standard | |
| page | 34 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |