CUED Publications database

Transition location effects on normal shock wave-boundary layer interactions

Davidson, TSC and Babinsky, H (2015) Transition location effects on normal shock wave-boundary layer interactions. In: UNSPECIFIED.

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© 2015 by Todd Davidson and Holger Babinsky. Published by the American Institute of Aeronautics and Astronautics, Inc. This paper reports recent work undertaken to investigate the interaction between normal shocks and laminar/transitional boundary layers. Laminar ow is desirable for its low skin friction, but problems are expected with shock interactions as the boundary layer will be prone to separation. Experiments have been performed on a at plate to explore the fundamental interaction without complex geometries and ow fields, and on a transonic aerofoil to research the in uence of the imposed pressure field. The boundary layer state before the shock on the at plate does not appear to significantly affect the downstream ow development, contrary to expectations, as the laminar separation is so small. On the aerofoil, a similar result is observed, with no change in the buffet onset Mach number. This implies that normal shock wave-laminar boundary layer interactions are not as detrimental as originally feared, and are in fact quite benign.

Item Type: Conference or Workshop Item (UNSPECIFIED)
Divisions: Div A > Fluid Mechanics
Depositing User: Cron Job
Date Deposited: 17 Jul 2017 19:39
Last Modified: 22 May 2018 07:36