CUED Publications database

Experimental investigation of 3D shock / boundary layer interaction control in transonic flows

Ogawa, H and Babinsky, H (2006) Experimental investigation of 3D shock / boundary layer interaction control in transonic flows. Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting, 14. pp. 10486-10497.

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Abstract

A novel supersonic wind tunnel setup is proposed to enable the investigation of control on a normal shock wave. Previous experimental arrangements were found to suffer from shock instability. Wind tunnel tests with and without control have confirmed the capability of the new setup to stabilise a shock structure at a target position without changing the nature of the shock wave / boundary layer interaction flow at M∞ = 1.3 and M ∞ = 1.5. Flow visualisation and pressure measurements with the new setup have revealed detailed characteristics of shock wave / boundary layer interactions and a λ-shock structure as well as benefits of control in total drag reduction in the presence of 3D bump control.

Item Type: Article
Subjects: UNSPECIFIED
Divisions: Div A > Fluid Mechanics
Depositing User: Cron Job
Date Deposited: 07 Mar 2014 13:04
Last Modified: 27 Nov 2014 19:21
DOI: