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Author : C.R. Traas
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (842 download)
Download or read book Blunt Body Supersonic Flow written by C.R. Traas and published by . This book was released on 1967 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Richard W. Barnwell
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Time-dependent Method for Calculating Supersonic Blunt-body Flow Fields with Sharp Corners and Embedded Shock Waves written by Richard W. Barnwell and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Hyman Harvey Album
Publisher :
ISBN 13 :
Total Pages : 164 pages
Book Rating : 4.E/5 ( download)
Download or read book Spiked Blunt Bodies in Supersonic Flow written by Hyman Harvey Album and published by . This book was released on 1961 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt: The force and moment characteristics of spiked bodies with hemispherical, hemispherical-flat, and flat noses were determined in a supersonic wind tunnel at angles of attack from zero to 10 degrees. The afterbodies were right circular cylinders. A fineness ratio of 3 was maintained for all of the basic bodies. The spikes were of five different configurations and ranged in length from 0.75 to 2.0 body diameters. Freestream conditions included Mach numbers from 2.0 to 3.0 and Reynolds numbers from 300,000 to 900,000 (based on body diameter). It was found that the spikes greatly reduced the zero-angle drag, made the drag extremely sensitive to angle of attack variations, substantially increased the lift, and also increased the normal force. The body nose shape proved to be a critical factor in determining the magnitude of these characteristics and whether or not the spikes would have a stabilizing effect on the body pitching moment characteristics. (Author).
Author : G. Moretti
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.3/5 (91 download)
Download or read book Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack written by G. Moretti and published by . This book was released on 1968 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Comparisons are made between the cylindrical and polar coordinate system used in determining the three-dimensional shock layer flow over the nose region of a blunted supersonic vehicle. Jusfification for the development of a polar coordinate system is given and an outline for such development is presented. Results from the polar coordinate system are given as is the limiting useful range.
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Author :
Publisher :
ISBN 13 :
Total Pages : 53 pages
Book Rating : 4.:/5 (966 download)
Download or read book Spiked Blunt Bodies in Supersonic Flow [with List of References] written by and published by . This book was released on 1961 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John David Anderson (Jr.)
Publisher :
ISBN 13 :
Total Pages : 78 pages
Book Rating : 4.3/5 (91 download)
Download or read book On Hypersonic Blunt Body Flow Fields Obtained with a Time-dependent Technique written by John David Anderson (Jr.) and published by . This book was released on 1968 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: New results are presented for inviscid, supersonic and hypersonic blunt-body flow fields obtained with a numerical time-dependent method patterned after that of Moretti and Abbett. In addition, important comments are made with regard to the physical and numerical nature of the method. Specifically, numerical results are presented for two-dimensional and axisymmetric parabolic and cubic blunt bodies as well as blunted wedges and cones; these results are presented for zero degrees angle of attack and for a calorically perfect gas with gamma = 1.4. The numerical results are compared with other existing theoretical and experimental data. Also, the effects of initial conditions and boundary conditions are systematically examined with regard to the convergence of the time-dependent numerical solutions, and the point is made that the initial conditions can not be completely arbitrary. Finally, in order to learn more about the performance of the time-dependent method, a numerical experiment is conducted to examine the unsteady propagation and region of influence of a slight pressure disturbance introduced at a point on the surface of a blunt body.
Author : Jerry Curtis South
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.:/5 (31 download)
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:
Author : S. M. Gilinskiĭ
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Method for Computing Supersonic Flow Around Blunt Bodies, Accompanied by a Detached Shock Wave written by S. M. Gilinskiĭ and published by . This book was released on 1965 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Milton Van Dyke
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.:/5 (31 download)
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.
Author : Goetz H. Klopfer
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (317 download)
Download or read book Numerical Study of Unsteady Viscous Hypersonic Blunt Body Flows with an Impinging Shock written by Goetz H. Klopfer and published by . This book was released on 1988 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Charles Paul Gardiner
Publisher :
ISBN 13 :
Total Pages : 110 pages
Book Rating : 4.:/5 (259 download)
Download or read book An Iterative Integral Technique for Supersonic Blunt Body Flow written by Charles Paul Gardiner and published by . This book was released on 1965 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Milton Van Dyke
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (317 download)
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 36 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.
Author : James M. Kendall
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (841 download)
Download or read book Experiments on Supersonic Blunt-body Flows written by James M. Kendall and published by . This book was released on 1959 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Wolfgang E. Moeckel
Publisher :
ISBN 13 :
Total Pages : 668 pages
Book Rating : 4.F/5 ( download)
Download or read book Flow Separation Ahead of Blunt Bodies at Supersonic Speeds written by Wolfgang E. Moeckel and published by . This book was released on 1951 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic flow against blunt bodies placed in boundary layers is discussed, and it is concluded that wedge-shaped or conical dead-air regions should form ahead of the body for some ranges of body thickness. Analysis of this type of flow indicates that a maximum body thickness exists (relative to initial boundary-layer thickness) beyond which steady wedge-type or conical separation regions cannot occur. For the range of relative body thicknesses for wihch wedge-type separation occurs, good agreement was obtained between experimental and theoretical pressures in the dead-air region at Mach numbers from 1.73 to 2.02. Unsteady flow was obtained for large relative body thickness.
Author : S. M. Gilinskii
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (227 download)
Download or read book Method for Calculation of Supersonic Flow Past Blunt Bodies with a Detached Shock Wave written by S. M. Gilinskii and published by . This book was released on 1968 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The paper deals with the development of a method for calculating supersonic flow past blunt bodies with a detached shock wave. The first section contains a formulation of the problem of supersonic flow past a blunt body of an arbitrary shape and an investigation of basic gas-dynamics equations. A method is given for the selection of a differential system for solving a boundary problem. This is followed by sections on the construction of an algorithm for the numerical solution of a boundary value problem in a mixed region and on the method of solving a nonlinear problem. The final section gives examples illustrating the solution of different problems of flow past bodies of different shapes with a detached shock wave. (Author).
Author : Richard W. Barnwell
Publisher :
ISBN 13 :
Total Pages : 84 pages
Book Rating : 4.:/5 (31 download)
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.
Author : Nikolaĭ Fedorovich Krasnov
Publisher : Elsevier Publishing Company
ISBN 13 :
Total Pages : 930 pages
Book Rating : 4.3/5 (91 download)
Download or read book Aerodynamics of Bodies of Revolution written by Nikolaĭ Fedorovich Krasnov and published by Elsevier Publishing Company. This book was released on 1970 with total page 930 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive technical treatise is provided on the aerodynamics of bodies of revolution from transonic to hypersonic speeds, covering all aspects of the subject, including transonic flow, linearized supersonic flow, Newtonian flow, rarefield gas and free-molecule flow, skin friction, heat transfer, and mass transfer. This English translation of a unique Russian textbook is provided with some corrections, references for all sources the editor could identify, redrawn figures, and an editor's introduction to each chapter summarizing and referencing pertinent material that has appeared since 1964, when the second edition was published. Krasnov's general approach assumes knowledge of the basic gas dynamic equations and applies them to solve aerodynamic problems. All important methods and techniques in modern aerodynamic theory are developed, with the aim of presenting practical methods for solving engineering problems. Results are usually given in the form of working equations, graphs, tables, or detailed sequential calculation methods. (Author).
