Triple–Shock–Wave Configurations: Comparison of Different Thermodynamic Models for Diatomic Gases

Mostovykh, Pavel S.; Усков, В. Н.

doi:10.1007/978-3-642-25685-1_144

Cited by 3 publications

(2 citation statements)

References 5 publications

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“…The zero-order problem is confined to determination of the flow downstream the shock parameters: pressure p, density ρ, velocity polar angle Θ and magnitude V , and the discontinuity inclination angle σ and the flow deflection angle β. Since the shock intensity J and its inclination angle σ for the given incoming flow parameters are interdependent (for instance, Mostovykh & Uskov 2011), the shock can be specified by any of these values; this fact is used later on. Note that in the zero-order problem the input parameters Θ and χ influence only on the angle Θ value:…”

Section: Differential Dynamic Compatibility Conditions On Shock Wavesmentioning

confidence: 99%

“…, A 8 , B 1 , B 2 in these expansions for different gases are cited in (McBride et al 1963;McBride, Gordon & Reno 1993). This model was previously considered by the authors in (Uskov & Mostovykh 2011). In this paper, oxygen is taken as a calorically imperfect gas; a comparison of its enthalpy and entropy with a diatomic perfect gas is shown in figure 2.…”

Section: Consequentlymentioning

confidence: 99%

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The flow gradients in the vicinity of a shock wave for a thermodynamically imperfect gas

Усков

Mostovykh

2015

Shock Waves

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Supersonic vortex plane and axisymmetric flows of non-viscous non-heatconductive gas with arbitrary thermodynamic properties in the vicinity of a steady shock wave are studied. The differential equations describing the gas flow exterior to the discontinuity surface and the dynamic compatibility conditions at this discontinuity are used. The gas flow nonuniformity in the shock vicinity is described by the space derivatives of the gasdynamic parameters at a point on the shock surface. The parameters are the gas pressure, density, velocity vector. The derivatives with respect to the directions of the streamline and normal to it, and of the shock surface and normal to it are considered. Space derivatives of all gasdynamic parameters are expressed through the flow nonisobaric factor along the streamline, the streamline curvature, and the flow vorticity and non-isoenthalpy factors. An algorithm for these factors of the gas flow downstream a shock wave determination is developed. Examples of these factors calculation for imperfect oxygen and thermodynamically perfect gas are presented. The influence coefficients of the upstream flow factors on the downstream flow factors are calculated. As an illustration for flows with upstream Mach number 5 it is shown that the flow vorticity factor is the most influenced by the thermodynamical gas properties. The gas flow in the vicinity of the shock is described by the isolines of gasdynamic parameters. Uniform plane and axisymmetric flows on different distances from the axis of symmetry are examined; the isobars, isopycnics, isotachs and isoclines are used to characterize the downstream flow behind a curved shock in an imperfect gas.

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Section: Differential Dynamic Compatibility Conditions On Shock Wavesmentioning

confidence: 99%

Section: Consequentlymentioning

confidence: 99%

The flow gradients in the vicinity of a shock wave for a thermodynamically imperfect gas

Усков

Mostovykh

2015

Shock Waves

Self Cite

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show abstract

Trends in the development of detonation engines for high-speed aerospace aircrafts and the problem of triple configurations of shock waves. Part II - Research of counterpropagating shock waves and triple shock wave configurations

Булат¹,

Денисенко²

2016

Naučno-teh. vestn. inf. tehnol. meh. opt.

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Mach Reflection of a Shock Wave from the Symmetry Axis of the Supersonic Nonisobaric Jet

Булат¹,

Усков²

2014

RJASET

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Triple–Shock–Wave Configurations: Comparison of Different Thermodynamic Models for Diatomic Gases

Cited by 3 publications

References 5 publications

The flow gradients in the vicinity of a shock wave for a thermodynamically imperfect gas

The flow gradients in the vicinity of a shock wave for a thermodynamically imperfect gas

Trends in the development of detonation engines for high-speed aerospace aircrafts and the problem of triple configurations of shock waves. Part II - Research of counterpropagating shock waves and triple shock wave configurations

Mach Reflection of a Shock Wave from the Symmetry Axis of the Supersonic Nonisobaric Jet

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