Supersonic gas flow past a cylindrical obstacle on a plate

Calculation of the Flow Pattern and the Heat Fluxes in the Interaction of a Shock Wave with a Cylinder in a Supersonic Flow

“…In this case, the boundary layer thickness δ was taken to be equal to δ /d = 0.05. The calculated configuration of the separation zone is satisfactorily confirmed by the experimental data obtained in [3] for M = 3.1 and Re L = 1.87 · 10 7 (the experimental data are given in parentheses): separation zone length in the plane of symmetry l s /d ≈ 1.95 (∼ 2.0), separation zone length-to-width ratio l s /l m ≈ 0.46 (∼ 0.5), and "critical shock" inclination angle θ s ≈ 26 • (∼ 25 • ). The flow under consideration is characterized by the fact is that it is streamlines lying considerably above the pre-separation boundary layer that arrive in the shock interaction region ahead of the cylinder and then in the separation zone.…”

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The problem of determining the mechanical and thermal action on a cylinder in a supersonic flow with account for the interference between an incident shock and the detached bow shock has been studied extensively, both experimentally and theoretically, in the last few decades [1][2][3][4][5][6][7][8][9][10][11][12]. A fairly complete survey can be found in monograph [12].

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“…Such flows were studied in detail in experiments [3][4][5][6]. The technique for calculating the peak pressure and heat transfer levels proposed above is extended to this case below.…”

Interaction between an Inclined Shock and Boundary and High-Entropy Layers on a Flat Plate

“…Finally, at the end of the sixties essentially three-dimensional interference flows, for example, on a plate ahead of a cylindrical obstacle, were investigated [17][18][19][20]. These investigations showed that a supersonic flow closed by a shock can develop inside the three-dimensional separation zone.…”

Experimental investigation of supersonic flow over a hemisphere

“…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 …”