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NACA-TN-3071
Theoretical supersonic force and moment coefficients on a sideslipping vertical- and horizontal-tail combination with subsonic leading edges and supersonic trailing edges
Year: 1954
Abstract: Theoretical expressions have been derived by means of linearized supersonic-flow theory for the lateral force due to sideslip CYβ, the yawing moment due to sideslip Cnβ, and the rolling moment due to sideslip Clβ for tail arrangements consisting of a vertical triangular surface attached to a symmetrical triangular horizontal surface. The results are valid, in general, for a range of Mach number for which the leading edges of the tail surfaces are swept behind the Mach cone from the apex of the arrangement and the trailing edges of the tail surfaces are ahead of the Mach lines from the tips.
A series of design charts are presented which permit rapid estimates to be made of the force and moment derivatives. A discussion is also included on the application of the expressions for the pressure distributions determined herein to other plan-form shapes of the tail surfaces and possible wing-vertical-tail arrangements. A solution to a two-dimensional "mixed type" boundary-value problem which is needed in the present analysis but which may also be of interest in other "conical flow" analyses is presented in an appendix.
A series of design charts are presented which permit rapid estimates to be made of the force and moment derivatives. A discussion is also included on the application of the expressions for the pressure distributions determined herein to other plan-form shapes of the tail surfaces and possible wing-vertical-tail arrangements. A solution to a two-dimensional "mixed type" boundary-value problem which is needed in the present analysis but which may also be of interest in other "conical flow" analyses is presented in an appendix.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:32:47Z | |
| date available | 2017-09-04T16:32:47Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | USNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/96244 | |
| description abstract | Theoretical expressions have been derived by means of linearized supersonic-flow theory for the lateral force due to sideslip CYβ, the yawing moment due to sideslip Cnβ, and the rolling moment due to sideslip Clβ for tail arrangements consisting of a vertical triangular surface attached to a symmetrical triangular horizontal surface. The results are valid, in general, for a range of Mach number for which the leading edges of the tail surfaces are swept behind the Mach cone from the apex of the arrangement and the trailing edges of the tail surfaces are ahead of the Mach lines from the tips. A series of design charts are presented which permit rapid estimates to be made of the force and moment derivatives. A discussion is also included on the application of the expressions for the pressure distributions determined herein to other plan-form shapes of the tail surfaces and possible wing-vertical-tail arrangements. A solution to a two-dimensional "mixed type" boundary-value problem which is needed in the present analysis but which may also be of interest in other "conical flow" analyses is presented in an appendix. | |
| language | English | |
| title | NACA-TN-3071 | num |
| title | Theoretical supersonic force and moment coefficients on a sideslipping vertical- and horizontal-tail combination with subsonic leading edges and supersonic trailing edges | en |
| type | standard | |
| page | 83 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |