CUED Publications database

Experimental and computational investigations of a normal-hole-bled supersonic boundary layer

Oorebeek, JM and Babinsky, H and Ugolotti, M and Orkwis, P and Duncan, S (2015) Experimental and computational investigations of a normal-hole-bled supersonic boundary layer. AIAA Journal, 53. pp. 3726-3736. ISSN 0001-1452

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© 2015 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc. Aseries of experiments have been conducted on a bleed hole array spanning the width of the Cambridge University Engineering Department supersonic wind tunnel at Mach numbers of 1.8 and 2.5. The wind tunnel was run with varying levels of suction, and the flow structure over the bleed array was subsequently mapped with a laser Doppler velocimetry system at a resolution of 0.25 hole diameters or better. The same wind-tunnel setup was simulated using the OVERFLOW Navier-Stokes equation solver. The information obtained was used primarily in qualitative comparisons of flow patterns. Overall good agreement was found in the definition of the expansion fan and barrier shock pattern produced by flow entering the normal holes, as well as three-dimensional flow patterns. Both studies agreed well in terms of measured mass flow rates, to within 1% of the boundary-layer mass flow. The presence of the barrier shock standing off the downstream edge of the bleed holes corresponded with a jet of upward flow, which may provide a mechanism for the generation of streamwise vortices.

Item Type: Article
Divisions: Div A > Fluid Mechanics
Depositing User: Cron Job
Date Deposited: 17 Jul 2017 19:35
Last Modified: 19 Jul 2018 08:57