Summary
An experimental investigation was carried out to study the unsteadiness related to shock?wave/boundary-layer interaction flowfield using a two-dimensional 24° compression ramp model in a 8.94 Mach flow with air as test gas. All the tests were carried out at a charge tube pressure of 50 bar and To=773 K, corresponding to a unit Reynolds number of 2.078 × 105 m-1. Off-surface analysis of the complete interactive flowfield is made using a Laser Schlieren system that measures time-dependent voltage signals representative of the fluctuating density gradient field. An array of 16 very-high-response photodiodes arranged on a 1 mm pitch were used for multichannel measurements. Analysis shows the shock-legs close to the model surface to vary in intensity and exhibit axial movement in accordance to the expansion and contraction movement of the separation bubble.
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© 2002 Springer-Verlag Berlin Heidelberg
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Verma, S.B., Koppenwallner, G. (2002). Study of Shock–Wave/Boundary–Layer Interaction Flowfield on a 24° Ramp Model. In: Wagner, S., Rist, U., Heinemann, HJ., Hilbig, R. (eds) New Results in Numerical and Experimental Fluid Mechanics III. Notes on Numerical Fluid Mechanics (NNFM), vol 77. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45466-3_18
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DOI: https://doi.org/10.1007/978-3-540-45466-3_18
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-53642-7
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