A method for measuring recompression shock unsteadiness applied to two supersonic wakes |
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| Authors: | Alan L Kastengren J Craig Dutton Gregory S Elliott |
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| Institution: | (1) Department of Mechanical and Industrial Engineering, University of Illinois at Urbana-Champaign, 1206 West Green Street, Urbana, IL 61801, USA;(2) Mechanical and Aerospace Engineering Department, The University of Texas at Arlington, Box 19018, Arlington, TX 76019, USA;(3) Department of Aerospace Engineering, University of Illinois at Urbana-Champaign, 104 South Wright Street, Urbana, IL 61801, USA |
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| Abstract: | The recompression shock system in blunt-base cylinder wakes at 0° and 10° angles-of-attack to an M=2.46 freestream is visualized by planar laser scattering, allowing the instantaneous position of the shock to be determined over a wide region of the flow. The recompression shock at  =0° is highly branched and appears to be quite weak. The shock appears to be stronger at =10°, with far less branching. Correlation analysis for the =10° wake indicates that fluctuations in the shock position tend to be correlated over relatively long streamwise distances. Analysis of the shock angle for the angle-of-attack wake shows a significant variation in the local angle of the shock, with trends similar to those seen for the unsteadiness in the shock position. |
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