Download or read book Interference on Axisymmetric Bodies in Subsonic Flow written by J. Reid and published by . This book was released on 1977 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computational and Experimental Aerodynamic Interference Study of Axisymmetric Bodies at Subsonic Speeds written by Fred W. Martin and published by . This book was released on 1980 with total page 125 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program has been formulated for the study of the mutual aerodynamic interference between axisymmetric bodies. The basic approach utilizes the method of superposition of an axial source-sink distribution to form closed bodies. The mutual interference flow fields are then superimposed on the isolated body solutions. This work has been limited, therefore, to solutions of the Prandtl-Glauert equation. An operational computer program available as a result of contractual work previously for the U.S. Air Force, has been appropriately revised for this work. In addition to the analytical effort, a limited amount of experimental data has been obtained for the dual purpose of obtaining an experimental data base and of verifying the validity of the analytical work.
Download or read book Aerodynamic Interference of Two Axisymmetric Stores at Low Supersonic Speeds written by John E. Burkhalter and published by . This book was released on 1976 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Supersonic Flow Past a Family of Blunt Axisymmetric Bodies written by Milton Van Dyke and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some 100 numerical computations have been carried out for unyawed bodies of revolution with detached bow waves. The gas is assumed perfect with y=5/3, 7/5, or 1. Free-stream Mach numbers are taken as 1.2, 1.5, 2, 3, 4, 6, 10, and [infinity symbol]. The results are summarized with emphasis on the sphere and paraboloid.
Download or read book Second order Slender body Theory written by Milton Van Dyke and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes.
Download or read book Aerodynamic Interference of Wing pylon body Combinations at Low Subsonic Speeds written by Kenneth Boland Walkley and published by . This book was released on 1973 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Download or read book Reverse Flow and Supersonic Interference written by Brown University. Division of Engineering and published by . This book was released on 1958 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Time dependent Method for Calculating Supersonic Angle of attack Flow about Axisymmetric Blunt Bodies with Sharp Shoulders and Smooth Nonaxisymmetric Blunt Bodies written by Richard W. Barnwell and published by . This book was released on 1971 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A time-dependent numerical method for calculating supersonic flow about blunt bodies at large angles of attack is presented. The axisymmetric bodies with sharp shoulders which are treated are constructed with a generator composed of segments of constant curvature. The nonaxisymmetric bodies have continuous slope and curvature. All flow fields are inviscid and adiabatic and have one plane of symmetry. A modification to the method of characteristics is introduced for use at the shock wave. A two-step finite-difference method of second-order accuracy is used at the body surface and in the region between the shock and body. A new finite-difference technique is introduced for use at sharp sonic shoulders. Comparisons of the results of the present method with experiment and the results of other methods are made for the flow of equilibrium air past the Apollo command module at the trim angle of attack and for perfect gas flow past a spherical cap and a spherically blunted cone at angle of attack. Both the cap and the blunted cone are terminated with sharp shoulders. Results are presented also for perfect gas flow past a prolate spheroid with its major axis normal to the flow.
Download or read book Jet Interaction Control Effectiveness for Subsonic and Supersonic Flight written by Louis A. Cassel and published by . This book was released on 1969 with total page 420 pages. Available in PDF, EPUB and Kindle. Book excerpt: Interference effects between a highly underexpanded, sonic or supersonic jet in a subsonic or supersonic crossflow, and the surface from which the jet exhausts are examined. For subsonic freestream Mach numbers, existing data are examined and correlated. Various semi-empirical models to represent the interference pressure distribution on flat plates are then developed. For supersonic freestream Mach numbers, a computer program for calculating jet interference effects on axisymmetric bodies at angle of attack is described. Interference effects between the jet plume and control fins on a cruciform missile are analyzed. A semi-empirical model of the jet in a crossflow, valid at large distances from the nozzle is developed. The results of this model are then used to compute interference forces and moments on fins located aft of the nozzle, both for subsonic and for supersonic freestream Mach numbers.
Download or read book Calculation of Axisymmetric Supersonic Flow Past Blunt Bodies with Sonic Corners written by Jerry Curtis South and published by . This book was released on 1968 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Generation of Axisymmetric Bodies in Subsonic Flow by Means of Complex Singularities written by D.M. Metcalf and published by . This book was released on 1982 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Flow Over Axisymmetric and Non axisymmetric Bodies written by Jefferson Fong and published by . This book was released on 1986 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Flow Past a Family of Blunt Axisymmetric Bodies written by and published by . This book was released on 1959 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Inviscid Stability of Supersonic Flow Past Heated Or Cooled Axisymmetric Bodies written by Institute for Computer Applications in Science and Engineering and published by . This book was released on 1990 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Flow Past Family of Blunt Axisymmetric Bodies with List of References written by and published by . This book was released on 1959 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Calculation of Supersonic Axisymmetric Afterbody Flow with Jet interference and Possible Flow Separation written by Robert A. White and published by . This book was released on 1974 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies written by George D. Catalano and published by . This book was released on 2001-09 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational fluid dynamics (CFD) approach to predicting high- speed aerodynamic flow fields of interest to the U.S. Army Research Laboratory (ARL) has been carried out The aerodynamic problems of particular interest are: (1) supersonic flow past the aftbody of projectiles with base mass injection, (2) supersonic flow past the M549 projectile, and (3) subsonic, transonic, and supersonic flow past an M864 projectile with base bleed and wake combustion. The commercially available FLUENT (Fluent, Inc. FLUENT. Version 5.1.1, Lebanon, NH, 1999.) CFD code was utilized. The computational effort supports an ongoing ARL- sponsored experimental investigation. Of particular interest in the present investigation is the careful characterization of the various turbulence models employed in the CFD code. Additionally, the ease of use and set-up as well as the computational time will be described. An experimental effort (Dutton, J. C., and A. L. Addy. 'Fluid Dynamic Mechanisms and Interactions Within Separated Flows'. U.S. Army Research Office Research Grant DAAH04-93-G-0226 and the Department of Mechanical and Industrial Engineering, University of illinois, Urbana-Champagne, Urbana, IL, August 1998.) consisting of detailed laser Doppler velocimeter (LDV), particle image velocimeter (PIV), and high-speed wall pressure measurements has been made in axisymmetric and planar subsonic and supersonic flows with embedded separated regions. The present work seeks to predict similar flow fields computationally and to address areas of agreement and disagreement.
