Supersonic Flow Past A Family Of Blunt Axisymmetric Bodies
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Supersonic Flow Past A Family Of Blunt Axisymmetric Bodies
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Author : Milton Van Dyke
language : en
Publisher:
Release Date : 1959
Supersonic Flow Past A Family Of Blunt Axisymmetric Bodies written by Milton Van Dyke and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Aerodynamics, Supersonic categories.
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.
Supersonic Flow Past A Family Of Blunt Axisymmetric Bodies
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Author : Milton Van Dyke
language : en
Publisher:
Release Date : 1959
Supersonic Flow Past A Family Of Blunt Axisymmetric Bodies written by Milton Van Dyke and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Aerodynamics, Supersonic categories.
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.
Calculation Of Axisymmetric Supersonic Flow Past Blunt Bodies With Sonic Corners
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Author : Jerry Curtis South
language : en
Publisher:
Release Date : 1968
Calculation Of Axisymmetric Supersonic Flow Past Blunt Bodies With Sonic Corners written by Jerry Curtis South and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with Mathematical models categories.
A Time Dependent Method For Calculating Supersonic Angle Of Attack Flow About Axisymmetric Blunt Bodies With Sharp Shoulders And Smooth Nonaxisymmetric Blunt Bodies
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Author : Richard W. Barnwell
language : en
Publisher:
Release Date : 1971
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Finite differences categories.
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.
Second Order Slender Body Theory
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Author : Milton Van Dyke
language : en
Publisher:
Release Date : 1959
Second Order Slender Body Theory written by Milton Van Dyke and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Aerodynamics categories.
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.
Difference Methods For Initial Boundary Value Problems And Flow Around Bodies
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Author : You-lan Zhu
language : en
Publisher: Springer Science & Business Media
Release Date : 2013-06-29
Difference Methods For Initial Boundary Value Problems And Flow Around Bodies written by You-lan Zhu and has been published by Springer Science & Business Media this book supported file pdf, txt, epub, kindle and other format this book has been release on 2013-06-29 with Mathematics categories.
Since the appearance of computers, numerical methods for discontinuous solutions of quasi-linear hyperbolic systems of partial differential equations have been among the most important research subjects in numerical analysis. The authors have developed a new difference method (named the singularity-separating method) for quasi-linear hyperbolic systems of partial differential equations. Its most important feature is that it possesses a high accuracy even for problems with singularities such as schocks, contact discontinuities, rarefaction waves and detonations. Besides the thorough description of the method itself, its mathematical foundation (stability-convergence theory of difference schemes for initial-boundary-value hyperbolic problems) and its application to supersonic flow around bodies are discussed. Further, the method of lines and its application to blunt body problems and conical flow problems are described in detail. This book should soon be an important working basis for both graduate students and researchers in the field of partial differential equations as well as in mathematical physics.
Numerical Analysis Of Flow Properties About Blunt Bodies Moving At Supersonic Speeds In An Equilibrium Gas
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Author : Harvard Lomax
language : en
Publisher:
Release Date : 1964
Numerical Analysis Of Flow Properties About Blunt Bodies Moving At Supersonic Speeds In An Equilibrium Gas written by Harvard Lomax and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Aerodynamics, Supersonic categories.
Calculation Of Supersonic Flow Past Bodies Supporting Shock Waves Shaped Like Elliptic Cones
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Author : Benjamin R. Briggs
language : en
Publisher:
Release Date : 1959
Calculation Of Supersonic Flow Past Bodies Supporting Shock Waves Shaped Like Elliptic Cones written by Benjamin R. Briggs and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Numerical analysis categories.
Numerical Solutions For Blunt Axisymmetric Bodies In A Supersonic Spherical Source Flow
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Author : Mamoru Inouye
language : en
Publisher:
Release Date : 1966
Numerical Solutions For Blunt Axisymmetric Bodies In A Supersonic Spherical Source Flow written by Mamoru Inouye and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Aerodynamics, Supersonic categories.
Flow Field Study About A Hemisphere Cylinder In The Transonic And Low Supersonic Mach Number Range
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Author : T. Hsieh
language : en
Publisher:
Release Date : 1975
Flow Field Study About A Hemisphere Cylinder In The Transonic And Low Supersonic Mach Number Range written by T. Hsieh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1975 with Aerodynamics, Transonic categories.
A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.