Large-eddy simulation of shock-turbulence interaction in supersonic diffuser flows

ABSTRACT

LES based on explicit filtering is used to study the shock train phenomenon in turbulent supersonic diffuser flows with circular cross-section and isothermal wall with an incoming pipe flow at friction Reynolds number 245 and centerline Mach number 1.7. Alternate regions of compression and expansion are found in the shock train which is followed by a shock-free ‘mixing’ region as observed in experiments and simulations in the literature. Turbulence amplification and local peaks in pressure-dilatation correlation are observed in the vicinity of the shocks. Low-frequency oscillations of the shock train are also observed.

KEYWORDS:

• LES
• shock train
• diffuser flow

Acknowledgements

The authors gratefully acknowledge the financial support of Aeronautical Research and Development Board (AR&DB) (grant number 1741), India for this work. S.G. gratefully acknowledges the discussions with Prof Rainer Friedrich of TU, Munich on this topic.

Disclosure statement

No potential conflict of interest was reported by the authors.

Additional information

Funding

Aeronautical Research and Development Board (AR&DB) [grant number 1741], India.