Aerodynamic Interference Between Stores PDF Download
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Author: F. Carroll Dougherty
Publisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 40
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Book Description
Author: F. Carroll Dougherty
Publisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 40
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Book Description
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 : 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: John E. Burkhalter
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 70
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Book Description
A method for determining the basic pressure distribution on an axisymmetric body in supersonic flow has been evaluated. Supersonic line sources with linearly varying strengths placed along the centerline of the body were used to generate the body shape. The results of these theoretical computations for an isolated body agreed very well with experimental data. Two approaches were investigated to determine the pressure distribution on two bodies interfering with each other. In the first approach supersonic point sources were placed along an image line, as determined by subsonic theory, and along the body centerline. The strengths of these point sources were determined so that body boundary conditions were met on top and bottom of each interfering body. Computational problems were encountered with this techniuqe resulting from the nature of induced velocities from a supersonic point source and the approach was finally abandoned. The second interference approach utilized linearly varying line sources placed along an image line and along the body centerline. The location of the image line is solely a function of the delta-x interval chosen for the problem. As before, body boundary conditions were met on top and on bottom of each interfering body. The results of these computations appear realistic for thin bodies.
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel. Symposium
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 306
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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: United States. Naval Air Systems Command
Publisher:
ISBN:
Category : Aeronautics, Military
Languages : en
Pages : 174
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Book Description
Author: Nik Ahmad Ridhwan Nik Mohd.
Publisher: Springer Nature
ISBN: 9819968747
Category : Technology & Engineering
Languages : en
Pages : 280
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Book Description
This book consists of selected peer-reviewed papers from the 2nd International Seminar on Aeronautics and Energy (ISAE 2022) focusing on the theme to revive the aviation industry post-COVID-19 pandemic. The topics discussed in this book include aircraft design and optimization, computational fluid dynamics (CFD) simulation and experimental aerodynamics, aircraft structure and aeroelasticity, guidance control and navigation, aircraft manufacturing and health monitoring avionics and system integration of UAV/drones, SITL AND HITL application on drones, rockets and missile, industrial wind engineering, green fuel and aviation sustainability, and aviation management. This book is a valuable resource for academicians and industry players in the field of aviation and sustainability.
Author: Bertha M. Ryan
Publisher:
ISBN:
Category : Weapons systems
Languages : en
Pages : 82
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Book Description
