22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-3.5.1

SHOCK WAVE/BOUNDARY LAYER INTERACTION

J. Müller, R. Mümmler, W. Staudacher
University of the German Armed Forces – Trisonic Windtunnel Munich, Germany

Keywords: shock / boundary layer / separation / supersonic / laser doppler anemometer

Experiments based on laser Doppler anemometry (LDA) were performed to investigate shock/boundary layer interaction in the presence of separation. Applicability and limits of this experimental method are briefly discussed. Experiments are concentrated on flow conditions given by M = 2.5/Re = 29·106 m-1, interaction is generated by an unswept, 2-d flat plate/24 degree ramp configuration. Time averaged locations of separation, reattachment and the mean shock position are determined by measurements in closest proximity to the surfaces. Results are compared with data from pressure measurements given in literature.

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