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Experiments on transitional shock wave--boundary layer interactions at Mach 5

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Abstract

An experimental campaign was carried out to investigate transitional shock wave--boundary layer interactions (SWBLI) at Mach and unit Reynolds numbers of 5 and 15.9 × 106 1/m, respectively. An impinging shock that generates 7° flow deflection resulted in separated SWBLI flowfield on axisymmetric centrebody. Various flow diagnostics were utilised such as schlieren photography, quantitative infrared thermography, shear sensitive liquid crystals, pressure sensitive paints and particle image velocimetry (PIV) to provide a complete time-averaged experimental data set. One nominally laminar case (with triggered transition due to SWBLI) and four natural transition cases with varying intermittency were tested. Heat transfer and shear stress peaks occurred around the reattachment point. For nominally laminar case, the separation induces transition, and thus, heat transfer and pressure peaks were found to be the highest. For the cases with natural transition with different intermittency levels, where incoming boundary layer is in state of transition, the magnitude of pressure and heat transfer peaks initially started to increase reaching a maximum and afterwards decreased towards the highest intermittency case. The presence of streamwise vortices was apparent for laminar case. Pressure peaks were found to occur slightly downstream of heat flux/shear stress peaks. PIV results (for laminar case only) showed high levels of turbulence above the separation region, proving triggered transition behaviour.

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Acknowledgments

The test models were designed by Dr. Nalleli Gongora-Orozco; her and Mr. Mark Quinn’s help during the test campaign is greatly acknowledged. The authors would like to thank the technical staff at University of Manchester for their help and assistance. This work has been conducted for European Space Agency (ESA) with a TRP reference number of 2009/666/MPA.

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Authors and Affiliations

  1. AeroPhysics Laboratory, School of Engineering, University of Glasgow, Glasgow, G12 8QQ, UK

    E. Erdem & K. Kontis

  2. Fluid Gravity Engineering, The Old Coach House, 1 West Street, Emsworth, 10 7DX, UK

    E. Johnstone

  3. European Space Research and Technology Centre, Postbus 299, Keplerlaan 1, 2200 AG, Noordwijk, The Netherlands

    N. P. Murray & J. Steelant

Authors
  1. E. Erdem
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  2. K. Kontis
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  3. E. Johnstone
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  4. N. P. Murray
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  5. J. Steelant
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Correspondence to K. Kontis.

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Erdem, E., Kontis, K., Johnstone, E. et al. Experiments on transitional shock wave--boundary layer interactions at Mach 5. Exp Fluids 54, 1598 (2013). https://doi.org/10.1007/s00348-013-1598-z

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  • DOI: https://doi.org/10.1007/s00348-013-1598-z

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