Supersonic Flow Past A Family Of Blunt Axisymmetric Bodies

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Supersonic Flow Past a Family of Blunt Axisymmetric Bodies

Milton Van Dyke,Helen D. Gordon
Supersonic Flow Past a Family of Blunt Axisymmetric Bodies Book PDF

Author : Milton Van Dyke,Helen D. Gordon
Publisher : Unknown
Page : 32 pages
File Size : 43,8 Mb
Release : 1959
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106908426

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Supersonic Flow Past a Family of Blunt Axisymmetric Bodies by Milton Van Dyke,Helen D. Gordon Pdf

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

Milton Van Dyke,Helen D. Gordon
Supersonic Flow Past a Family of Blunt Axisymmetric Bodies Book PDF

Author : Milton Van Dyke,Helen D. Gordon
Publisher : Unknown
Page : 25 pages
File Size : 40,5 Mb
Release : 1959
Category : Aerodynamics, Supersonic
ISBN : OCLC:34621234

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Supersonic Flow Past a Family of Blunt Axisymmetric Bodies by Milton Van Dyke,Helen D. Gordon Pdf

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

Milton Van Dyke,Helen D. Gordon
Supersonic Flow Past a Family of Blunt Axisymmetric Bodies Book PDF

Author : Milton Van Dyke,Helen D. Gordon
Publisher : Unknown
Page : 36 pages
File Size : 45,9 Mb
Release : 1959
Category : Aerodynamics, Supersonic
ISBN : NASA:31769000420003

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Supersonic Flow Past a Family of Blunt Axisymmetric Bodies by Milton Van Dyke,Helen D. Gordon Pdf

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.

A Time-dependent Method for Calculating Supersonic Angle-of-attack Flow about Axisymmetric Blunt Bodies with Sharp Shoulders and Smooth Nonaxisymmetric Blunt Bodies

Richard W. Barnwell
A Time dependent Method for Calculating Supersonic Angle of attack Flow about Axisymmetric Blunt Bodies with Sharp Shoulders and Smooth Nonaxisymmetric Blunt Bodies Book PDF

Author : Richard W. Barnwell
Publisher : Unknown
Page : 84 pages
File Size : 45,9 Mb
Release : 1971
Category : Finite differences
ISBN : UIUC:30112106881557

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A Time-dependent Method for Calculating Supersonic Angle-of-attack Flow about Axisymmetric Blunt Bodies with Sharp Shoulders and Smooth Nonaxisymmetric Blunt Bodies by Richard W. Barnwell Pdf

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

Milton Van Dyke
Second order Slender body Theory Book PDF

Author : Milton Van Dyke
Publisher : Unknown
Page : 36 pages
File Size : 54,6 Mb
Release : 1959
Category : Aerodynamics
ISBN : NASA:31769000420979

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Second-order Slender-body Theory by Milton Van Dyke Pdf

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

You-lan Zhu,Xi-chang Zhong,Bing-mu Chen,Zuo-min Zhang
Difference Methods for Initial Boundary Value Problems and Flow Around Bodies Book PDF

Author : You-lan Zhu,Xi-chang Zhong,Bing-mu Chen,Zuo-min Zhang
Publisher : Springer Science & Business Media
Page : 606 pages
File Size : 52,9 Mb
Release : 2013-06-29
Category : Mathematics
ISBN : 9783662067079

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Difference Methods for Initial-Boundary-Value Problems and Flow Around Bodies by You-lan Zhu,Xi-chang Zhong,Bing-mu Chen,Zuo-min Zhang Pdf

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.

Flow-field Study about a Hemisphere-cylinder in the Transonic and Low Supersonic Mach Number Range

T. Hsieh,W. T. Strike,B. M. Majors
Flow field Study about a Hemisphere cylinder in the Transonic and Low Supersonic Mach Number Range Book PDF

Author : T. Hsieh,W. T. Strike,B. M. Majors
Publisher : Unknown
Page : 64 pages
File Size : 53,6 Mb
Release : 1975
Category : Aerodynamics, Transonic
ISBN : UOM:39015104953073

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Flow-field Study about a Hemisphere-cylinder in the Transonic and Low Supersonic Mach Number Range by T. Hsieh,W. T. Strike,B. M. Majors Pdf

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.

NASA Technical Paper

Anonim
NASA Technical Paper Book PDF

Author : Anonim
Publisher : Unknown
Page : 316 pages
File Size : 53,5 Mb
Release : 1990
Category : Astronautics
ISBN : MINN:31951P00131666V

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NASA Technical Paper by Anonim Pdf

NASA Technical Note

Anonim
NASA Technical Note Book PDF

Author : Anonim
Publisher : Unknown
Page : 714 pages
File Size : 47,5 Mb
Release : 1974
Category : Electronic
ISBN : MINN:319510008465172

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NASA Technical Note by Anonim Pdf

Hypersonic Inviscid Flow

Wallace D. Hayes,Ronald F. Probstein
Hypersonic Inviscid Flow Book PDF

Author : Wallace D. Hayes,Ronald F. Probstein
Publisher : Courier Corporation
Page : 628 pages
File Size : 42,7 Mb
Release : 2012-07-13
Category : Science
ISBN : 9780486160481

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Hypersonic Inviscid Flow by Wallace D. Hayes,Ronald F. Probstein Pdf

Unified, self-contained view of nonequilibrium effects, body geometries, and similitudes available in hypersonic flow and thin shock layer; appropriate for graduate-level courses in hypersonic flow theory. 1966 edition.