Numerical and Experimental Examination of Shock Control Bump Flow Physics

K. Nübler (), S. P. Colliss, T. Lutz, H. Babinsky and E. Krämer
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K. Nübler: IAG Universität Stuttgart
S. P. Colliss: University of Cambridge, Aerodynamics Laboratory
T. Lutz: IAG Universität Stuttgart
H. Babinsky: University of Cambridge, Aerodynamics Laboratory
E. Krämer: IAG Universität Stuttgart

A chapter in High Performance Computing in Science and Engineering ‘12, 2013, pp 333-349 from Springer

Abstract: Abstract A method allowing a detailed investigation of the flow physics of shock control bumps (SCBs) on an unswept airfoil has been developed by comparison of the results of experiments and computations. A simple wind tunnel set-up is proposed which is shown to generate representative baseline conditions, allowing fine details of the flow to be measured using an array of techniques. Computational data for the same bump configuration is then validated against the experimental results, allowing a more intimate analysis of the flow physics as well as relating wind tunnel results to the performance of the SCB on an unswept wing.

Keywords: Wind Tunnel; Flow Physic; Shock Position; Pressure Sensitive Paint; Supersonic Wind Tunnel (search for similar items in EconPapers)
Date: 2013
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-642-33374-3_25

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DOI: 10.1007/978-3-642-33374-3_25

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