On the numerical construction of shock-wave fronts

Kraiko, A. N.; Makarov, V. E.; Tillyaeva, N. N.

doi:10.1016/0041-5553(80)90316-x

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Results Of the Numerical Solution Of Unsteady Euler Equation1

Steady Separation Zone On a Blunt Nose1

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1982

2014

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Cited by 9 publications

(2 citation statements)

References 6 publications

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“…21. The boundary condition on the right-hand boundary, i.e., an arc of the circle r = 1, was specified using a technique that was first applied in Ref.…”

Section: Results Of the Numerical Solution Of Unsteady Euler Equationmentioning

confidence: 99%

The flow of a supersonic ideal gas with “weak” and “strong” shocks over a wedge

Kraiko¹,

P’yankov²,

Yakovlev³

2014

Journal of Applied Mathematics and Mechanics

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“…21. The boundary condition on the right-hand boundary, i.e., an arc of the circle r = 1, was specified using a technique that was first applied in Ref.…”

Section: Results Of the Numerical Solution Of Unsteady Euler Equationmentioning

confidence: 99%

The flow of a supersonic ideal gas with “weak” and “strong” shocks over a wedge

Kraiko¹,

P’yankov²,

Yakovlev³

2014

Journal of Applied Mathematics and Mechanics

Self Cite

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“…In the regions of smooth flow parameter distributions this scheme ensures the second-order approximation of the governing differential equations on near-uniform grids. In this example, the bow shock was fitted using the ideas set out in [23].…”

Section: Steady Separation Zone On a Blunt Nosementioning

confidence: 99%

Ideal gas flows with separation zones and time-dependent contact discontinuities of complicated shape

Kraiko¹,

P’yankov²

2006

Fluid Dyn

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Some examples of flows with separation zones and movable contact discontinuities obtained as a result of the numerical integration of the time-dependent equations for an ideal gas are presented. The examples concern a steady annular separation zone on the blunt nose of a body in a supersonic flow, periodic shedding of unsteady discontinuities from a cylinder in a steady uniform subsonic flow with a supercritical Mach number, and the complicated deformation of a contact (tangential) discontinuity, namely, the boundaries of a two-dimensional jet, either subsonic or supersonic, flowing into a cocurrent subsonic low-velocity flow. A multiple increase in the difference grid capacity in the numerical integration of the Euler equations indicates the absence of a noticeable scheme viscosity effect in the examples calculated. The inviscid nature of the separation flows obtained is also confirmed by their well-known counterparts constructed in the ideal incompressible fluid approximation. The time-average velocity fields of the two-dimensional jet and the intensity of its sound field are in reasonable agreement with the available data.

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Calculation of supersonic gas flow over a ducted body in regimes with a detached shock wave

Tillyaeva¹

1982

Fluid Dyn

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On the numerical construction of shock-wave fronts

Cited by 9 publications

References 6 publications

The flow of a supersonic ideal gas with “weak” and “strong” shocks over a wedge

The flow of a supersonic ideal gas with “weak” and “strong” shocks over a wedge

Ideal gas flows with separation zones and time-dependent contact discontinuities of complicated shape

Calculation of supersonic gas flow over a ducted body in regimes with a detached shock wave

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