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Flow visualization of Mach 3 compression ramp with different upstream boundary layers

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Abstract

Experimental studies of supersonic flow over several compression ramps are carried out in a Mach 3.0 wind tunnel; the upstream boundary layers include laminar flow, transitional flow, and turbulent flow. Fine flow structures are obtained via nano-tracer planar laser scattering (NPLS) technique, typical flow structures such as boundary layer, shear layer, and shock wave are visible distinctly. The angle of shock wave and the development of boundary layer are measured by time-averaged flow field, the spatiotemporal evolutions of flow field are revealed by two time-dependent NPLS images. Results indicate that when ramp angles are 25°, a typical separation occurs in laminar flow, and a certain extent separation occurs in transitional flow, while separation does not occur in turbulent flow. When ramp angles are 28°, laminar flow separates further, a typical separation occurs in transitional flow, by comparison, separation region in turbulent flow is small. Significant differences of the three types of ramp flows can be found in shock wave structure and flow separation.

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References

  • Ardonceau PL (1984) The structure of turbulence in a supersonic shock-wave/boundary layer interaction. AIAA J 22(9):1254–1262

    Article  Google Scholar 

  • Bleilebens M, Olivier H (2006) On the influence of elevated surface temperatures on hypersonic shock wave boundary layer interaction at a heated ramp model. Shock Waves 15:301–312

    Article  Google Scholar 

  • Bookey P, Wyckham C (2005) New experimental data of STBLI at DNS/LES accessible Reynolds numbers. AIAA Paper 2005-0309

  • Chen Z, Yi S, He L, Zhu Y, Ge Y, Wu Y (2014) Spatial density fluctuation of supersonic flow over a backward-facing step measured by nano-tracer planar laser scattering. J Vis 17(4):345–361

    Article  Google Scholar 

  • Disimile PJ, Scaggs NE (1989) An investigation into wedge induced turbulent boundary layer separation on a uniformly roughened surface at Mach 6. AIAA Paper 1989-2163

  • Dolling D, Or C (1985) Unsteadiness of the shock wave structure in attached and separated compression ramp flows. Exp Fluids 3:24–32

    Article  Google Scholar 

  • Ganapathisubramani B, Clemens N, Dolling D (2006) Planar imaging measurements to study the effect of spanwise structure of upstream turbulent boundary layer on shock induced separation. AIAA Paper 2006-0324

  • Ganapathisubramani B, Clemens N, Dolling D (2009) Low-frequency dynamics of shock-induced separation in a compression ramp interaction. J Fluid Mech 636:397–425

    Article  MATH  Google Scholar 

  • Gang D, Yi S, Wu Y, Zhu Y (2014) Supersonic flow over circular protuberances on a flat plate. J Vis 17(4):307–317

    Article  Google Scholar 

  • Holden M, Chadwick K (1995) Studies of laminar, transitional and turbulent hypersonic flows over curved compression surfaces. AIAA Paper 1995-0093

  • Law CH (1975) Supersonic shock wave-turbulent boundary layer interactions. AIAA Paper 1975-0832

  • Lee C, Wang S (1995) Study of the shock motion in a hypersonic shock system/turbulent boundary layer interaction. Exp Fluids 19:143–149

    Google Scholar 

  • Lewis JE, Kubota T, Lees L (1967) Experimental investigation of supersonic laminar, two dimensional boundary layer separation in a compression corner with and without cooling. AIAA Paper 1967-0191

  • Martin M, Smits A, Wu M, Ringuette M (2006) The turbulence structure of shockwave and boundary layer interaction in a compression corner. AIAA Paper 2006-0497

  • Prince SA, Vannahme M, Stollery JL (1999) Experiments on the hypersonic turbulent shock-wave/boundary layer interaction and the effects of surface roughness. AIAA Paper 1999-0147

  • Quan P, Yi S, Wu Y, Zhu Y, Chen Z (2014) Experimental investigation of interactions between laminar or turbulent boundary layer and shock wave. Acta Phys Sin 63(8):084703

    Google Scholar 

  • Ringuette M, Bookey P, Wyckham C, Smits A (2009) Experimental study of a Mach 3 compression ramp interaction at Reθ = 2400. AIAA J 47:373–385

    Article  Google Scholar 

  • Settles GS, Fitzpatrick TJ, Bogdonoff SM (1979) Detailed study of attached and separated compression corner flow fields in high Reynolds number supersonic flow. AIAA J 17(6):579–585

    Article  Google Scholar 

  • Simeonides G, Haase W, Manna M (1994) Experimental, analytical and computational methods applied to hypersonic compression ramp flows. AIAA J 32(2):301–310

    Article  Google Scholar 

  • Wu Y, Yi S, Chen Z, Zhang Q, Gang D (2013) Experimental investigations on structures of supersonic laminar/turbulent flow over a compression ramp. Acta Phys Sin 62(18):184702

    Google Scholar 

  • Yi S, He L, Zhao Y, Tian L, Cheng Z (2009) A flow control study of a supersonic mixing layer via NPLS. Sci China 52:2001–2006

    Article  Google Scholar 

  • Zhang Q, Yi S, Chen Z, Zhu Y, Zhou Y (2013) Visualization of supersonic flow over double wedge. J Vis 16:209–217

    Article  Google Scholar 

  • Zhao Y, Yi S, Tian L, He L, Cheng Z (2009) Supersonic flow imaging via nanoparticles. Sci China 52:3640–3648

    Article  MATH  Google Scholar 

  • Zhu Y, Yi S, He L, Tian L, Zhou Y (2013) Instantaneous and time-averaged flow structures around a blunt double-cone with or without supersonic film cooling visualized via nano-tracer planar laser scattering. Chin Phys B 22:014702

    Article  Google Scholar 

Download references

Acknowledgments

This research is supported by the National Natural Science Foundation of China (No. 11172326 and 11302256).

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Authors and Affiliations

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

    Yu Wu, Shihe Yi, Lin He, Zhi Chen & Yangzhu Zhu

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  1. Yu Wu
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  2. Shihe Yi
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  3. Lin He
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  4. Zhi Chen
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  5. Yangzhu Zhu
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Correspondence to Lin He.

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Wu, Y., Yi, S., He, L. et al. Flow visualization of Mach 3 compression ramp with different upstream boundary layers. J Vis 18, 631–644 (2015). https://doi.org/10.1007/s12650-014-0255-9

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  • DOI: https://doi.org/10.1007/s12650-014-0255-9

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