CUED Publications database

Three-dimensional shock control bumps: Effects of geometry

Bruce, PJK and Colliss, SP and Babinsky, H (2014) Three-dimensional shock control bumps: Effects of geometry. In: UNSPECIFIED.

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Abstract

© 2015, American Institute of Aeronautics and Astronautics Inc. All rights reserved. Results from wind tunnel experiments with three different geometry shock control bumps (SCBs) are presented and discussed. The primary aims of this study are to explore how 3-D SCBs generate stream-wise vorticity and to compare the flow features produced by different geometry 3-D SCBs. Results are presented in two parts: In part I, the flow development over a simple geometry baseline bump is described in detail with a focus on describing the evolution of vortical flow structures. In part II, results from tests with two different bumps (with subtle geometric variations from the baseline design) are presented and compared with those from the baseline bump. It is observed that the mechanism of vortex production for all 3-D SCBs tested is broadly in agreement with that reported in literature: Specifically, vortical flow structures are only observed downstream of the crest, on the SCB tail. Differences between the three SCB geometries tested are relatively subtle; increasing the width of the SCB tail reduces the extent of shock-induced separation at the crest, giving an anticipated reduction in viscous drag; steepening the SCB sides also reduces shock-induced separation at the crest (although to a lesser extent) and modifies the pressure profile on the off the bump such that the flow experiences lower span-wise pressure gradients. These findings suggest both geometric modifications considered may yield a benefit in performance for a 3-D SCB mounted on a transonic wing.

Item Type: Conference or Workshop Item (UNSPECIFIED)
Subjects: UNSPECIFIED
Divisions: Div A > Fluid Mechanics
Depositing User: Cron Job
Date Deposited: 17 Jul 2017 19:44
Last Modified: 03 Aug 2017 03:14
DOI: