Skip to main content
SpringerLink
Log in

Effect of micro-ramps on supersonic boundary layer past a double wedge

  • Short Paper
  • Published:
Journal of Visualization Aims and scope Submit manuscript

Abstract

The effect of micro-ramps on Mach 3 boundary layer structures past a double wedge was experimentally investigated in a supersonic low-noise wind tunnel using nano-tracer planar laser scattering (NPLS) technique. The fine structures of supersonic flow over the double wedge with and without the micro-ramps, as well as temporal and spatial evolutionary characteristics of the vortex structures with the micro-ramps, were revealed.

Graphical abstract

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5

References

  • Adrian RJ (2007) Hairpin vortex organization in wall turbulence. Phys Fluids 19:041301

    Article  MATH  Google Scholar 

  • Ashill PR, Fulker JF, Hackett K C (2002) Studies of flows induced by sub boundary layer vortex generators (SBVGs) AIAA paper 2002-0968

  • Babinsky H, Li Y, Ford CWP (2009) Microramp control of supersonic oblique shock-wave/boundary-layer interactions. AIAA J 47(3):668–675

    Article  Google Scholar 

  • Giepman RHM, Schrijer FFJ, Oudheusden BW (2014) Flow control of an oblique shock wave reflection with micro-ramp vortex generators: effects of location and size. Phys Fluids 26:066101

    Article  Google Scholar 

  • Quan PC, Yi SH, Wu Y, Zhu YZ, He L (2015) Experimental investigation on the effects of swept angles on blunt fin-induced flow. AIAA J 53(9):2805–2810

    Article  Google Scholar 

  • Schrijer FFJ, Scarano F, van Oudheusden BW (2006) Application of PIV in a Mach 7 double-ramp flow. Exp Fluids 41:353–363

    Article  Google Scholar 

  • Wang B, Liu WD, Zhao YX, Fan XQ, Wang C (2012) Experimental investigation of the micro-ramp based shock wave and turbulent boundary layer interaction control. Phys Fluids 24:055110

    Article  Google Scholar 

  • Wu Y, Yi SH, He L, Chen Z, Zhu YZ (2015) Flow visualization of Mach 3 compression ramp with different upstream boundary layers. J Vis 18(3):631–644

    Article  Google Scholar 

Download references

Acknowledgements

This study was supported by the National Natural Science Foundation of China (Grant no. 11502280).

Author information

Authors and Affiliations

  1. Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang, China

    Zhang Qinghu, Xu Xiaobin, Wang Xiong, Lin Jingzhou & Tong Hua

Authors
  1. Zhang Qinghu
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Xu Xiaobin
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Wang Xiong
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Lin Jingzhou
    View author publications

    You can also search for this author in PubMed Google Scholar

  5. Tong Hua
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Zhang Qinghu.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Qinghu, Z., Xiaobin, X., Xiong, W. et al. Effect of micro-ramps on supersonic boundary layer past a double wedge. J Vis 21, 1–4 (2018). https://doi.org/10.1007/s12650-017-0441-7

Download citation

  • Received:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12650-017-0441-7

Keywords

Search

Navigation