Interference Effects Due to Vortex Sheets According to Slender Body Theory PDF Download
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Author: A. von Baranoff
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: A. von Baranoff
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1246
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Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 702
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Book Description
It is found that the impulse of each shed vortex and its image vortex in a transformed circle plane enters into all the interference forces and moments on the airplane. A simple theorem is given for the interference forces in steady straight flight which are found to depend on this impulse evaluated only at the wing trailing edge and at the base of the configuration.
Author: Frank S. Malvestuto (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 282
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Author:
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ISBN:
Category : Translations
Languages : en
Pages : 1008
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Author: J. Richard Spahr
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Book Description
A theoretical method based on slender-body theory is presented for the stepwise calculation of vortex paths in the presence of wing-body combinations and the determination of the load distributions, forces, and moments on the combinations due to the vortices. Comparisons of calculated and experimental results indicate that the vortex paths and the forces induced by the vortices can be closely predicted by the calculative method only for slender configurations. The total forces and moments, however, in many cases can be predicted adequately for nonslender as well as slender triangular-wing configurations.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1322
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 620
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 81
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Book Description
Mathematical expressions are derived for the interference forces and moments acting on the tails of slender plane and cruciform wing-tail combinations of general plan form in steady straight flight at combined angles of attack and sideslip. The derivatives are made within the limitations of slender-body theory under the assumption that the vortex sheet leaves the wing as flat sheet and becomes fully rolled up ahead of the tail. The derived expressions are used to calculate the steady lifts, side forces, pitching moments, and rolling moments of the number of wing-tail combinations. The effects of changes in tail height, tail length, ratio of tail span to wing span, tail incidence, and tail thickness are calculated. The resulting curves, and particularly their nonlinearities, are discussed at some length in connection with static stability. In general, the most dramatic effects are noted when the vortices shed from the wing strike the tips of the tail trailing edge.
