Fluid Dynamics

, Volume 53, Issue 1, pp 169–175 | Cite as

Visualization of Supersonic Low-Noise Flow Over Surface-Mounted Two-Dimensional Prisms

  • Xiaolin Liu
  • Sihe Yi
  • Dundian Gang
  • Xiaoge Lu


An experimental study of supersonic flow over two-dimensional surface-mounted prisms is carried out in a Mach 3 low-noise wind tunnel. The noise level of this supersonic wind tunnel, defined as the root mean-square Pitot pressure fluctuation normalized by the mean Pitot pressure, can be reduced to about 0.37%. The nanotracer planar laser scattering (NPLS) technique is used to analyze the influence of the prism geometry and the oncoming flow conditions on the typical flow structures including separation and reattachment shocks. With increase in the prism height the induced shocks move upstream. At a constant streamwise length L of a prism the timeaveraged NPLS images show that the length of the downstream recirculation region increases from 0.8L to 1.2L, when the prism height H changes from 3 to 5 mm. As compared with the flow structures occurring downstream of the prisms, the upstream flow structures are more susceptible to the oncoming boundary layer and are considerably different in laminar and turbulent flows. The separation shock wave is clearly visible in turbulent flow even for the 1-mm prism, whereas in the case of laminar flow there is no a distinct shock wave upstream of this prism. At the same time, the location of the flow reattachment and the angle of the reattachment shock wave in the downstream flow remain almost the same in both two flow regimes.

Key words

low-noise wind tunnel nanotracer planar laser scattering two-dimensional prisms flow separation and reattachment 


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  1. 1.
    J. Counihan, J. C. R. Hunt, and P. S. Jackson, “Wakes behind Two-Dimensional Surface Obstacles in Turbulent Boundary Layers,” J. Fluid Mech. 64, 529 (1974).ADSCrossRefGoogle Scholar
  2. 2.
    P. Castro, “Relaxing Wakes behind Surface-Mounted Obstacles in Rough Wall Boundary Layers,” J. Fluid Mech, 93, 631 (1979).ADSCrossRefGoogle Scholar
  3. 3.
    F. Durst and A. Rastogi, “Turbulent Flow over Two-Dimensional Fences,” Turbul. Shear Flows. 2, 218 (1980).zbMATHGoogle Scholar
  4. 4.
    G. Bergeles and N. Athanassiadis, “The Flow past a Surface-Mounted Obstacle,” J. Fluids Eng. 105, 461 (1983).CrossRefGoogle Scholar
  5. 5.
    C. D. Tropea and R. Gackstatter, “The Flow over Two-Dimensional Surface-Mounted Obstacles at Low Reynolds Numbers,” J. Fluids Eng. 107, 489 (1985).CrossRefGoogle Scholar
  6. 6.
    J. Antoniou and G. Bergeles, “Development of the Reattached Flow behind Surface-Mounted Two-Dimensional Prisms,” J. Fluids Eng. 110, 127 (1988).CrossRefGoogle Scholar
  7. 7.
    J.-H. Chou and S. Chao, “Branching of a Horseshoe Vortex around Surface-Mounted Rectangular Cylinders,” Exp. Fluids 28, 394 (2000).CrossRefGoogle Scholar
  8. 8.
    Q.-H. Zhang, S. H. Yi, Y. Z. Zhu, Z. Chen, and Y. Wu, “The Effect of Micro-Ramps on Supersonic Flow over a Forward-Facing Step,” Chin. Phys. Lett. 30 (2013).Google Scholar
  9. 9.
    Z. Chen, S. Yi, L. He, L. Tian, and Y. Zhu, “An Experimental Study on Fine Structures of Supersonic Laminar/Turbulent Flow over a Backward-Facing Step Based on NPLS,” Chin. Sci. Bull. 57, 584 (2012).CrossRefGoogle Scholar
  10. 10.
    Y.-Z. Zhu, S.-H. Yi, X.-P. Kong, P.-C. Quan, Z. Chen, and L.-F. Tian, “Fine Structures and the Uunsteadiness Characteristics of Supersonic Flow over Backward Facing Step via NPLS,” Acta Phys. Sin. 63 July (2014).Google Scholar
  11. 11.
    I. E. Beckwith, F. Chen, and M. R. Malik, “Design and Fabrication Requirements for Low Noise Supersonic/ HypersonicWind Tunnels,” in AIAA 26th Aerospace SciencesMeeting, Reno, Nevada, 1988 (1988).Google Scholar
  12. 12.
    S. P. Schneider, “The Development of Hypersonic Quiet Tunnels,” in 37th AIAA Fluid Dynamics Conference and Exhibit, Miami, FL, 2007 (2007).Google Scholar
  13. 13.
    I. Beckwith and C. G. Miller, “Aerothermodynamics and Transition in High-Speed Wind Tunnels at NASA Langley,” Annu. Rev. Fluid Mech. 22, 21 (1999).Google Scholar
  14. 14.
    S. P. Schneider and C. E. Haven, “Quiet-Flow Ludwieg Tube for High-Speed Transition Research,” AIAA J. 33, 688 (1995).ADSCrossRefGoogle Scholar
  15. 15.
    Y. X. Zhao, S. H. Yi, L. F. Tian, and Z. Y. Cheng, “Supersonic Flow Imaging via Nanoparticles,” Sci. China, Ser. E 52, 3640 (2009).CrossRefzbMATHGoogle Scholar

Copyright information

© Pleiades Publishing, Ltd. 2018

Authors and Affiliations

  1. 1.Department of Aerospace Science and Engineering National University of Defense TechnologyChangsha, HunanChina

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