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NACA-TN-2412
Theoretical force and moments due to sideslip of a number of vertical tail configurations at supersonic speeds
Year: 1951
Abstract: The tail configurations considered in this paper are sketched in figure 1. The orientation of the tail with respect to a body system of coordinate axes used in the analysis is shown in figure 2(a). Figure 2(b) shows a typical tail oriented with respect to the stability-axes System. The stability derivatives are generally evaluated in this system for stability studies.
The analysis is limited to tail configurations having surfaces of vanishingly small thickness and of zero camber. The vertical tail is assumed to be yawed an infinitesimal amount (ß→O); whereas the horizontal tail is always at zero geometric angle of attack. Essentially then, the vertical tail produces the disturbance velocities (similar to a wing at an angle of attack) and the horizontal tail acts as a barrier or end plate to the propagation of the vertical-tail disturbances(similar to end plate attached to lifting wing).
The analysis is limited to tail configurations having surfaces of vanishingly small thickness and of zero camber. The vertical tail is assumed to be yawed an infinitesimal amount (ß→O); whereas the horizontal tail is always at zero geometric angle of attack. Essentially then, the vertical tail produces the disturbance velocities (similar to a wing at an angle of attack) and the horizontal tail acts as a barrier or end plate to the propagation of the vertical-tail disturbances(similar to end plate attached to lifting wing).
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:49:00Z | |
| date available | 2017-09-04T18:49:00Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | ANKUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=autho1216AF6769B752731854DD6EFDEC014A/handle/yse/230339 | |
| description abstract | The tail configurations considered in this paper are sketched in figure 1. The orientation of the tail with respect to a body system of coordinate axes used in the analysis is shown in figure 2(a). Figure 2(b) shows a typical tail oriented with respect to the stability-axes System. The stability derivatives are generally evaluated in this system for stability studies. The analysis is limited to tail configurations having surfaces of vanishingly small thickness and of zero camber. The vertical tail is assumed to be yawed an infinitesimal amount (ß→O); whereas the horizontal tail is always at zero geometric angle of attack. Essentially then, the vertical tail produces the disturbance velocities (similar to a wing at an angle of attack) and the horizontal tail acts as a barrier or end plate to the propagation of the vertical-tail disturbances(similar to end plate attached to lifting wing). | |
| language | English | |
| title | NACA-TN-2412 | num |
| title | Theoretical force and moments due to sideslip of a number of vertical tail configurations at supersonic speeds | en |
| type | standard | |
| page | 61 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |