Mutual Aerodynamic Interference Effects for Multiple Bodies by the Cross-flow Corrections Method PDF Download
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Author: Fred W. Martin
Publisher:
ISBN:
Category : Cross-flow (Aerodynamics)
Languages : en
Pages : 66
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Book Description
The complexity of the flow field beneath an aircraft with external stores is examined analytically. Equations are produced for computing store separation trajectories, based on mutual interference flow fields between the aircraft and the store. The circle theorem and the small disturbances theory are used in establishing the perturbations responsible for the flow field interference. (Author).
Author: Fred W. Martin
Publisher:
ISBN:
Category : Cross-flow (Aerodynamics)
Languages : en
Pages : 66
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Book Description
The complexity of the flow field beneath an aircraft with external stores is examined analytically. Equations are produced for computing store separation trajectories, based on mutual interference flow fields between the aircraft and the store. The circle theorem and the small disturbances theory are used in establishing the perturbations responsible for the flow field interference. (Author).
Author: Kenneth Boland Walkley
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 120
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Book Description
A method for determining the subsonic aerodynamic interference between a planar wing with pylons and a single axisymmetric body has been developed and evaluated. The wing and body solutions were obtained independently using a simple horseshoe vortex system and a three-dimensional point source distribution, respectively. A vortex image system based on the two-dimensional theory of images was then added to the body to maintain the tangent-flow boundary condition in the non-uniform wing flow field. Both the influence of the vortex image system within the body and the body flow field effects at the wing were evaluated. No significant change in the wing vortex strength distribution resulted so that it was unnecessary to iterate the isolated wing solution. The theoretical results for incompressible flow were compared with pressure distributions obtained from low-speed wind tunnel tests of the wing-body configuration. The correlation was generally good. (Author).
Author: Fred W. Martin
Publisher:
ISBN:
Category : Cross-flow (Aerodynamics)
Languages : en
Pages : 62
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Book Description
The mutual aerodynamic interference problem for two axisymmetric bodies has been analyzed using the image system technique. In order to facilitate this analysis, it has been assumed that small perturbation solutions are valid. It is further assumed that the external stores are slender bodies and that the mutual interference can be analyzed by first assuming a cross-flow solution. The image system in the cross-flow plane consists of source-sink pairs appropriately located by using the Milne-Thomson circle theorem. The actual three-dimensional source-sink paris are displaced from the body axis according to the cross flow image system. Their strengths are then determined by the Rankine method. Good agreement has been found between the theoretical and experimental results. (Author).
Author: A. R. Rudnicki (Jr.)
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 170
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Book Description
Author: Bertha M. Ryan
Publisher:
ISBN:
Category : Weapons systems
Languages : en
Pages : 82
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Author: Fred W. Martin
Publisher:
ISBN:
Category : Base flow (Aerodynamics)
Languages : en
Pages : 120
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Book Description
A method of solution for the aerodynamic flow field about two bodies at angle of attack including mutual interference effects has been devised for bodies with circular cross-section. The analytical method used is a modification of a method of solution for the flow about axisymmetric bodies in close proximity at zero angle of attack. As a demonstration of this method, the flows about one, two and three finless M-117 bomb shapes were investigated. Theoretical pressure distributions are presented for the two and three body cases. For the three body case, experimental data is available; however, there is poor agreement with data thought primarily to be because of flow separation along the tails of the bombs. A non-axisymmetric modification of the M-117 bomb shape was developed in order to simulate the flow separation. The analytical results of this effort are compared with the experimental data. (Author).
Author: Fred W. Martin
Publisher:
ISBN:
Category : Cross-flow (Aerodynamics)
Languages : en
Pages : 112
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Book Description
The objective of this effort was to develop the theoretical solution required to define the mutual aerodynamic interference associated with the carriage and release of weapons in the multiple mode. The cross-flow solution for multiple axisymmetric bodies that was previously generated was used to correct the axisymmetric solution in order to account for the mutual interference effects. An equivalent cylindrical body was generated by conformal transformation in order to simulate, as if axisymmetric, the finned portions of the bodies. The analysis reported is for three M-117 bombs in the vicinity of a triple ejector rack; however, any axisymmetric, slender pointed weapon shape could be used. A limited amount of experimental work substantiating this theoretical solution is included as part of this effort. The resulting analytical solution has been programmed for use on both the IBM 360/50 and the CDC 6600 computers. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 312
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 648
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Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Author:
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 1002
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Book Description
