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Oblique-Shock Wave Boundary Layer Interactions Control

Shock Control Bumps

Book Chapter (2025)
Author(s)

Jane Bulut (TU Delft - Aerospace Engineering)

Ferry Schrijer (TU Delft - Aerospace Engineering)

Bas van Oudheusden (TU Delft - Aerospace Engineering)

Research Group
Aerodynamics
DOI related publication
https://doi.org/10.1007/978-3-031-86605-0_9 Final published version
More Info
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Publication Year
2025
Language
English
Research Group
Aerodynamics
Pages (from-to)
171-190
Publisher
Springer
ISBN (print)
['978-3-031-86604-3', '978-3-031-86607-4']
ISBN (electronic)
978-3-031-86605-0
Downloads counter
6
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Abstract

In this experimental study the effect of three-dimensional shock control bumps (SCB) on oblique shock wave/boundary layer interactions is investigated as a passive control method. It aims to develop an understanding of the effect of such devices on the interaction structure by means of studying the influence of the position of the bump with respect of the shock-impingement location, as well as the effect of the bump geometry (more in particular, the ramp section of the bump). The experiments were conducted in the ST-15 wind-tunnel at the Delft University of Technology for fully developed turbulent boundary layer conditions with Reθ of 21.8·103 and freestream Mach number of 2.0. The control effectiveness is assessed from the size of the separated flow region, as well as the downstream boundary layer velocity profile. For this, PIV is employed as the main diagnostic method to characterise the flow field. In addition to this, high-speed Schlieren and oil flow measurements were performed to asses the effect of the SCB on the overall interaction structure.