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Effect of height of microvortex generators on swept shock wave boundary layer interactions

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Abstract

A numerical study to evaluate the critical height of microvortex generators in controlling swept shock wave boundary layer interactions is carried out. The planar shock wave is generated by placing a 20° sharp fin in a supersonic flow at Mach 4. The ramp and thick vane microvortex generator geometries were considered. The device heights were varied from 30 to 90 % of the incoming boundary layer thickness. The efficacy of the devices was observed to increase with increasing device height up to a height of 70 % of the incoming boundary layer thickness beyond which no further improvement was achieved.

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Acknowledgments

The authors are thankful to the Vice Chancellor, Defence Institute of Advanced Technology (DIAT), Pune, India, for constant encouragement and support. The authors are also thankful to the Department of Computer Engineering and Department of Aerospace Engineering, DIAT, for the infrastructural support provided in conducting this study. The authors gratefully acknowledge Dr. Holger Babinsky of Cambridge University for providing results of his experiments and for several useful suggestions.

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  1. Defence Institute of Advanced Technology, Pune, India

    Roschelle R. Martis & Ajay Misra

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  1. Roschelle R. Martis
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  2. Ajay Misra
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Correspondence to Roschelle R. Martis.

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Martis, R.R., Misra, A. Effect of height of microvortex generators on swept shock wave boundary layer interactions. CEAS Aeronaut J 4, 315–326 (2013). https://doi.org/10.1007/s13272-013-0075-y

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  • DOI: https://doi.org/10.1007/s13272-013-0075-y

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