A Thin-shock-layer Solution for Nonequilibrium, Inviscid Hypersonic Flows in Earth, Martian, and Venusian Atmospheres
A Thin-shock-layer Solution for Nonequilibrium, Inviscid Hypersonic Flows in Earth, Martian, and Venusian Atmospheres

Author: William L. Gose

Publisher:

Published: 1971

Total Pages: 164

ISBN-13:

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An approximate inverse solution is presented for the nonequilibrium flow in the inviscid shock layer about a vehicle in hypersonic flight. The method is based upon a thin-shock-layer approximation and has the advantage of being applicable to both subsonic and supersonic regions of the shock layer. The relative simplicity of the method makes it ideally suited for programming on a digital computer with a significant reduction in storage capacity and computing time required by other more exact methods. Comparison of nonequilibrium solutions for an air mixture obtained by the present method is made with solutions obtained by two other methods. Additional cases are presented for entry of spherical nose cones into representative Venusian and Martian atmospheres. A digital computer program written in FORTRAN language is presented that permits an arbitrary gas mixture to be employed in the solution. The effects of vibration, dissociation, recombination, electronic excitation, and ionization are included in the program.

Inverse-method and Method-of-characteristics Flow-field Programs
Inverse-method and Method-of-characteristics Flow-field Programs

Author: J. B. Moreno

Publisher:

Published: 1967

Total Pages: 136

ISBN-13:

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Two flow-field computer codes are described. The codes were developed to compute the flow about blunt axisymmetric or two-dimensional bodies moving with supersonic speeds at zero angle of attack. Boundary-layer effects and a variety of thermochemical options are included. A pair of auxiliary codes for machine-plotting the flow-field results is also described.

The High Temperature Aspects of Hypersonic Flow
The High Temperature Aspects of Hypersonic Flow

Author: Wilbur C. Nelson

Publisher: Elsevier

Published: 2014-12-02

Total Pages: 801

ISBN-13: 1483223310

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The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.

Aerothermodynamic Consequences of Nozzle Nonequilibrium
Aerothermodynamic Consequences of Nozzle Nonequilibrium

Author: A. F. Burke

Publisher:

Published: 1966

Total Pages: 208

ISBN-13:

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The effects of nozzle nonequilibrium in a high temperature, hypersonic test facility were evaluated. By using the results of a set of exact computer solutions for air nozzle expansions to interpolate frozen atomic mole fraction and the fraction of total enthalpy frozen in dissociation and vibration, a method was devised for direct determination of (1) freestream quantities downstream of the freezing region in a nonequilibrium nozzle expansion, (2) the nozzle boundary layer growth, and (3) the aerodynamic effects of freestream nonequilibrium. The freestream results are shown to compare favorably with exact computer solutions. Illustrative applications to hypersonic inlet testing and downstream expansion following an MHD accelerator are included. (Author).

Difference Methods for Initial-Boundary-Value Problems and Flow Around Bodies
Difference Methods for Initial-Boundary-Value Problems and Flow Around Bodies

Author: You-lan Zhu

Publisher: Springer Science & Business Media

Published: 2013-06-29

Total Pages: 606

ISBN-13: 3662067072

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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.