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ISSN Online: 2688-7231

ISBN Online: 978-1-56700-524-0

Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India
December, 17-20, 2021, IIT Madras, Chennai, India

Effect of leading edge bluntness on the interaction of laminar boundary layer with induced shock wave

Get access DOI: 10.1615/IHMTC-2021.350
pages 237-242

Abstract

The area of high-speed flow is centered on shock waves and their interactions which vary the flow fields which alter the forces as well as heat loads on the bodies under negotiation. The interplay of various shocks with boundary layer formations is a common occurrence for the supersonic and hypersonic flow regimes. The interactions of boundary layer with an impinging shock wave (I-SWBLI) on a flat plate in the presence of sharp and leading edge bluntness have been investigated in the present studies. An in-house second-order accurate finite-volume based CFD solver has been utilized for the study of I-SWBLI and assessment of leading edge bluntness as a separation bubble size reduction method. For the array of bluntness radii deemed for current studies, it has been noted that the implementation of leading edge bluntness may offer a reduction in separation zone size in comparison to the sharp leading edge. Attempts were made to track the critical radii ('inversion radius') for trend reversal of the separation zone size, along with the 'equivalent radius' which is the limiting bluntness value for the given flow configurations with a free-stream Mach number of 2.0.
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