Experimental investigation of supersonic turbulent flow over cylinders with various heights

Gang, Dundian; Yi, Shihe; Niu, Haibo

doi:10.1007/s12650-020-00723-1

Cited by 7 publications

(1 citation statement)

References 21 publications

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“…Although it is difficult to ascertain the exact wall-normal extent of the three-dimensional flow region near the cylinder/sidewall junction without spanwise flow visualisation, it is reasonable to assume that this extent would be larger than the height of the incoming boundary layer thickness. In fact, a recent instantaneous flow visualisation of a Mach 3.8 flow over a cylinder with free end mounted to a wall (Gang, Yi & Niu 2021) appears to show sparse, but large coherent structures whose wall-normal extent can reach approximately twice the incoming boundary layer thickness (although the extent of the contribution of the free end to these structures is unclear). These facts imply that in the present case the wall-normal extent of the three-dimensional flow near the cylinder/wall junction may be somewhere between 15 % and 20 % of the test-section width.…”

Section: Experimental Set-upmentioning

confidence: 99%

Supersonic cylinder wake dynamics

et al. 2022

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The supersonic wake of a circular cylinder in Mach 3 flow was studied through high-speed, focussing schlieren photography. The mean and unsteady behaviour of the separated shear layers, the reattachment process, the recompression wave and the early wake are analysed, and discussed in detail. The fluctuations in the wake are stronger and more coherent than those within the approaching shear layers and the recirculation region. The recompression of the shear layers energises the finer scales in the flow which leads to a departure from a $-$ 1 spectral roll-off observed in the schlieren spectra further upstream. The recompression wave exhibits low-frequency unsteadiness and a ripple-type motion which occurs as it is perturbed by shocklets radiating from the coherent structures in the wake. The wake consists of coherent disturbances with the same characteristic frequency as that for an incompressible flow over a cylinder; however, this instability is suppressed as the wake accelerates, presumably due to increasing compressibility. The primary instability of the wake flow has a characteristic frequency nearly twice that of its incompressible counterpart and it is shown to be driven by the presence of aeroacoustic resonance in the wake. It is also shown that the resonance, which leads to the formation of broadband standing waves in the wake, is the result of an interaction between the wake instabilities and upstream propagating acoustic waves in the wake. The acoustic waves originate upstream of the reattachment region and are believed to be generated by the unsteady separation on the cylinder surface.

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Section: Experimental Set-upmentioning

confidence: 99%

Supersonic cylinder wake dynamics

et al. 2022

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Experimental study on the hypersonic boundary layer transition induced by tandem cylinders

Quan

et al. 2023

Experimental Thermal and Fluid Science

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Experimental investigation on evolution characteristics of high- and low-speed streaks in supersonic turbulent boundary layer

Han

2022

AIP Advances

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High-speed and low-speed streak structures in the near wall region of a turbulent boundary layer with a Mach number of 3 are experimentally examined by employing the spatiotemporally resolved nanoparticle plane laser scattering technique. The time evolution characteristics of the high-speed and low-speed streaks in the supersonic turbulent boundary layer are systematically investigated through the speed field sequence results at various time intervals. The obtained results reveal that the dynamic behavior of the bands is chiefly represented by the translation along the flow direction. The process of dissipation of the existing streaks and the formation of a new streak is also observed and analyzed. The duration values of the high-speed and low-speed streak structures are assessed by utilizing the time-resolved characteristics of the speed field, and the predicted duration of the streak structure and the maximum flow length exceed 306 µs and 23.6 times the thickness of the boundary layers, respectively. Finally, the merging phenomenon of medium and low-speed streaks in the turbulent boundary layer is carefully scrutinized. The merging of low-speed streaks observed under supersonic conditions is consistent with the vortex packet merging model proposed by Tomkins and Adrian.

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Experimental investigation of supersonic turbulent flow over cylinders with various heights

Cited by 7 publications

References 21 publications

Supersonic cylinder wake dynamics

Supersonic cylinder wake dynamics

Experimental study on the hypersonic boundary layer transition induced by tandem cylinders

Experimental investigation on evolution characteristics of high- and low-speed streaks in supersonic turbulent boundary layer

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