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Experimental investigation of supersonic turbulent flow over cylinders with various heights

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Abstract

The unsteady flow structures and pressure fluctuations of the cylinder-induced shock wave/boundary layer interactions (SBLIs) were investigated at Mach 3.4 and 3.8. The cylinders were mounted on the test section floor with a turbulent boundary layer, and six cylinders with various heights have been tested. The nanoparticle-based planar laser scattering (NPLS) flow visualization tests were performed, and the different features of shock systems as well as the "breath" effects of the separation bubble, have been validated by NPLS images. Dynamic pressure transducers were used to characterize the pressure fluctuations, and a remarkable spectra change was noticed around the cylinder foot. With increasing height, the PSD curve of x/D =  − 1 ahead of the cylinder shaped from one-peak pattern to two-peaks pattern, while the second frequency peak showed a typical frequency of f ≈32 kHz. It was inferred that the first peak was more influenced by the free end of the cylinder and the detached shock. The second peak pattern of f ≈32 kHz was presumed to be affected by the vortex breakdown near the cylinder foot through analysis of flow visualization. Low frequency around 0 ~ 3 kHz was found to have an obvious rise at x/D =  − 2, close to the typical frequency of SBLIs.

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References

  • Chandola G, Huang X, Estruch-Samper D (2017) Highly separated axisymmetric step shock-wave/turbulent-boundary-layer interaction. J Fluid Mech 828:236–270

    Article  Google Scholar 

  • Clemens NT, Narayanaswamy V (2013) Low-Frequency Unsteadiness Of Shockwave/Turbulent Boundary Layer Interactions. Annu Rev Fluid Mech 46:469–492

    Article  Google Scholar 

  • Dolling DS, Bogdonofff SM (1981) Scaling of interactions of cylinders with supersonic turbulent boundary layers. AIAA Journal 19:655–658

    Article  Google Scholar 

  • Dudley JG, Ukeiley L (2012) Numerical investigation of a cylinder immersed in a supersonic boundary layer. AIAA J 50:257–270

    Article  Google Scholar 

  • Erengil ME, Dolling DS (1991a) Unsteady wave structure near separation in a Mach 5 compression rampinteraction. AIAA J 29:728–735

    Article  Google Scholar 

  • Erengil ME, Dolling DS (1991b) Correlation of separation shock motion with pressure fluctuations inthe incoming boundary layer. AIAA J 29:1868–1877

    Article  Google Scholar 

  • Funderburk ML, Narayanaswamy V (2019) Experimental investigation of microramp control of an axisymmetric shock/boundary-layer interaction. AIAA J 57:3379–3394

    Article  Google Scholar 

  • Gang DD, Yi SH, He L (2016) Characteristics of the cylinder-induced shock wave and turbulent boundary layer interactions. J Vis 19:581–585

    Article  Google Scholar 

  • Hahn PV, Frendi A (2013) Interaction of three-dimensional protuberances with a supersonic turbulent boundary layer. AIAA J 51:1657–1666

    Article  Google Scholar 

  • Huang X, Estruch-Samper D (2018) Low-frequency unsteadiness of swept shock-wave/turbulent-boundary-layer interaction. J Fluid Mech 856:797–821

    Article  MathSciNet  Google Scholar 

  • Korkegi R (1971) Survey of viscous interactions associated with high mach number flight. AIAA J 9:771–784

    Article  Google Scholar 

  • Leidy AN, Neel IT, Tichenor NR, Bowersox RDW (2020) High-speed schlieren imaging of cylinder-induced hypersonic-shock-wave-boundary-layer interactions. Aiaa J 58:3090–3099

    Article  Google Scholar 

  • Niu HB, Yi SH, Liu XL, Lu XG, Gang DD (2020) Experimental investigation of boundary layer transition over a delta wing at Mach number 6. Chin J Aeronaut 33:1889–1902

    Article  Google Scholar 

  • Ozawa H, Laurence SJ (2018) Experimental investigation of the shock-induced flow over a wall-mounted cylinder. J Fluid Mech 849:1009–1042

    Article  Google Scholar 

  • Ozcan O, Holt M (1984) Supersonic separated flow past a cylindrical obstacle on a flat plate. AIAA J 22:611–618

    Article  Google Scholar 

  • Sedney R (1973) A survey of the effects of small protuberances on boundary-layer flows. AIAA J 11:782–792

    Article  Google Scholar 

  • Sedney R, Kitchens CW (1976) Measurement and correlation of separation ahead of protuberances in a turbulent boudary layer, In: AIAA 14th Aerospace sciences meetings, Washington DC

  • Sedney R, Kitchens CW (1977) Separation ahead of protuberances in supersonic turbulent boundary layers. AIAA J 15:546–552

    Article  Google Scholar 

  • Wang DP, Zhao YX, Xia ZX, Wang QH, Luo ZB (2012) Flow visualization of supersonic flow over a finite cylinder. Chin Phys Lett 29:084702

    Article  Google Scholar 

  • Wheaton BM, Bartkowicz MD, Subbareddy PK, Schneider SP (2011) Roughness-induced instabilities at mach 6: a combined numerical and experimental study. 41st AIAA Fluid Dynamics Conference and Exhibit, AIAA 2011–3248. Hawaii, Honolulu, p 28

    Google Scholar 

  • Zhao YX, Yi SH, He L, Cheng YZ, Tian LF (2007) The experimental study of interaction between shock wave and turbulence. Chinese Sci Bull 52:1297–1301

    Article  Google Scholar 

  • Zhao YX, Yi SH, Tian LF, He L, Cheng ZY (2009) Supersonic flow imaging via nanoparticles. Sci China Ser E 52:3640–3648

    Article  Google Scholar 

Download references

Acknowledgements

This work has been supported by the Natural Science Foundation of China (Grant Nos. 11902354).

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Authors and Affiliations

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073, Hunan, China

    Dundian Gang, Shihe Yi & Haibo Niu

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  1. Dundian Gang
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  2. Shihe Yi
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  3. Haibo Niu
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Correspondence to Dundian Gang.

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Gang, D., Yi, S. & Niu, H. Experimental investigation of supersonic turbulent flow over cylinders with various heights. J Vis 24, 461–470 (2021). https://doi.org/10.1007/s12650-020-00723-1

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  • DOI: https://doi.org/10.1007/s12650-020-00723-1

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