Supersonic viscous perfect gas flow past a circular cylinder

Bashkin, V. A.; Егоров, И. В.; Egorova, M. V.

doi:10.1007/bf01049787

Cited by 31 publications

(12 citation statements)

References 4 publications

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“…Sonic lines lie just inside the sliplines. This finding is corroborated by the computations of Bashkin et al (2000Bashkin et al ( , 2002. A sketch of the flow field with these features is shown in figure 3.…”

Section: Resultssupporting

confidence: 65%

“…Kim (1956) performed a similar study across a range of Mach numbers from 1.35 to 6.0. More recently numerical studies were performed by Bashkin et al (1998Bashkin et al ( , 2000Bashkin et al ( , 2002 with emphasis on the pressure and temperature distributions on the cylinder surface and the location of the separation point at various Mach and Reynolds numbers. To the authors' knowledge no experimental work has been performed to determine if there are oscillating flow features in the wake behind cylinders in supersonic flow as there are in subsonic flow.…”

Section: Introductionmentioning

confidence: 99%

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Oscillations in cylinder wakes at Mach 4

Schmidt

Shepherd

2015

J. Fluid Mech.

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The wake behind a circular cylinder in Mach 4 flow is examined experimentally in the Reynolds number range 2 × 10 4 to 5 × 10 5 . Periodic oscillations of the sliplines in the wake are observed. The Strouhal number of the oscillations based on the diameter of the cylinder is found to increase monotonically from 0.30 to 0.50 with increasing Reynolds number. If the Strouhal number is formed using the length of the sliplines, however, it has a constant value of approximately 0.48 for all Reynolds numbers studied. This scaling indicates that the oscillations in supersonic flow are likely driven by acoustic signals propagating back and forth through the subsonic region between the separation points on the cylinder and the neck where the sliplines converge, unlike in subsonic flow where oscillations are caused by vortices shed from the cylinder surface.

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Section: Resultssupporting

confidence: 65%

Section: Introductionmentioning

confidence: 99%

Oscillations in cylinder wakes at Mach 4

Schmidt

Shepherd

2015

J. Fluid Mech.

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“…In [10][11][12] methods of numerical analysis of the time-dependent two-dimensional Navier-Stokes equations were developed with reference to supersonic perfect gas flows.…”

Section: Numerical Simulation Of Laminar Flowmentioning

confidence: 99%

“…The system of nonlinear finite-difference equations is solved using a modified Newton method with formation of the Jacobi matrix by means of finite increments of the discrepancy vector with respect to the vector of the unknown grid variables. A more complete description of the numerical analysis technique is given in [10][11][12].…”

Section: Numerical Simulation Of Laminar Flowmentioning

confidence: 99%

Laminar heat exchange on sharp and blunt plates in a hypersonic air flow

Borovoi¹,

Егоров²,

Skuratov³

et al. 2005

Fluid Dyn

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The results of an experimental investigation and numerical simulation of heat exchange are given for sharp and blunt plates in a hypersonic air flow. The experiments were carried out in a Ludwig-type wind tunnel at hypersonic Mach numbers and a Reynolds number Re L which varied over the range from 0.24 · 10 6 to 1.31 · 10 6 . The bluntness radius r was varied over the range from 0.008 mm (almost sharp plate) to 4 mm (the corresponding Reynolds numbers Re r from 15 to 4 · 10 4 ). The numerical simulation was carried out by solving the complete two-dimensional Navier-Stokes equations. The experimental data were correlated using the well-known viscous hypersonic interaction parameters.

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“…Zhang [2] studied the interaction of the shock wave and boundary layer about the external flow and internal flow, and provided the photos of typical flow spectrums of different experimental models, including the photos of supersonic flow over a sphere. Some research institutions have studied the typical flow field structures of the supersonic flow over different models by means of experimental and numerical methods at home and abroad, and the models included the cylinder [3][4][5][6][7][8][9][10][11][12][13], the boss [5,6], the blunt fin [5,12], the wedge-shaped obstacle and sweptback step [13], and the cone [14,15], which were used to study the problems of the three-dimensional flow field structure, the interaction of the shock wave and the boundary layer, and boundary layer separation. Korkegi [16,17] and Sedney [18,19] surveyed and analyzed the experiments of supersonic flow over high and low protuberances.…”

mentioning

confidence: 99%

Experimental investigation of supersonic flow over a hemisphere

et al. 2012

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The experimental investigation of supersonic flow over a hemisphere was conducted using Nanoparticle-based Planar Laser Scattering (NPLS) technique in a supersonic quiet wind tunnel at Ma=2.68. Ahead of the hemisphere, boundary layer separation with the formation of a three-dimensional separated flow was observed, which was resulted from the interaction between the three-dimensional bow shock wave and the boundary layer. The complex flow structures of supersonic flow over the hemisphere were visualized. Based on the time correlation of NPLS images, time-space evolutionary characteristics of supersonic flow over the hemisphere were studied, and the evolutionary characteristics of the spanwise and streamwise large scale vortex structures were obtained, which have the features of periodicity and similar geometry. The protuberance is mounted on the surface or flow channel of the supersonic or hypersonic vehicle and the local structure of the flow field will be changed. Currently, achieving flow control has been becoming a research hotspot of supersonic flow. The study of the supersonic plate boundary layer and its interaction with the hemisphere has broad application background and high scientific value. The mutual interference of the hemisphere and supersonic flow generates complex flow field structures, which contain the three-dimensional detached shock wave, the surface topological structure, the circulating region in the downstream, the reattached shock wave and the wake. The complex flow field structures show the characteristics of the supersonic flow over a protuberance on the surface. Therefore the hemisphere can be used as a typical model to study the mechanism of the supersonic flow over a protuberance on the surface, and is also used to verify some questions that are disputed at present, such as the interaction of the three-dimensional curved shock wave and the boundary layer, the effect of the lateral pressure gradient on the surface flow spectrums and the dynamic characteristics of the supersonic vortical structure. Unfortunately, the influences of strong discontinuity and diffusion factors, such as compressibility, turbulence, large scale structure, shock waves and slip line, make it difficult to get the fine structure of supersonic flow over a hemisphere by means of high resolution numerical simulation and measurement. Hawthorne and Martin [1] studied the flow over a hemisphere on the flat plate by means of calculation method in 1955. Zhang [2] studied the interaction of the shock wave and boundary layer about the external flow and internal flow, and provided the photos of typical flow spectrums of different experimental models, including the photos of supersonic flow over a sphere. Some research institutions have studied the typical flow field structures of the supersonic flow over different models by means of experimental and numerical methods at home and abroad, and the models included the cylinder [3][4][5][6][7][8][9][10][11][12][13], the boss [5,6], the blunt fin [5,12], the wedge-shaped obstacle...

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Supersonic viscous perfect gas flow past a circular cylinder

Cited by 31 publications

References 4 publications

Oscillations in cylinder wakes at Mach 4

Oscillations in cylinder wakes at Mach 4

Laminar heat exchange on sharp and blunt plates in a hypersonic air flow

Experimental investigation of supersonic flow over a hemisphere

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