Cross-flow Corrected Axisymmetric Solution for Multiple Body Interference PDF Download
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Author: Fred W. Martin Publisher: ISBN: Category : Cross-flow (Aerodynamics) Languages : en Pages : 112
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: Fred W. Martin Publisher: ISBN: Category : Cross-flow (Aerodynamics) Languages : en Pages : 112
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: Fred W. Martin Publisher: ISBN: Category : Cross-flow (Aerodynamics) Languages : en Pages : 62
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: Kenneth Boland Walkley Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 120
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 : 66
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: Stephen C. Korn Publisher: ISBN: Category : Bomb racks Languages : en Pages : 272
Book Description
This report documents the external flow fields caused by various weapon configurations on the wing of an F-4 aircraft, verifies assumptions made in the flow angularity technique, and presents the documentation for the 'Flow Angularity Computer Program' with example trajectories. The flow angularity program is presently capable of calculating the trajectories of stores off the inboard and outboard wing stations in either single, triple ejector rack, or multiple ejector rack configurations. The assumptions made in the flow angularity technique have been analyzed and generally validated as good approximations. (Author).
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 456
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: Fred W. Martin
Author: Fred W. Martin
Author: Fred W. Martin
Author: Kenneth Boland Walkley
Author: Fred W. Martin
Author: A. R. Rudnicki (Jr.)
Author: Bertha M. Ryan
Author: Stephen C. Korn
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