Abstract
The wake flow behind a classical space launcher is highly unsteady and dominated by large-scale flow separation, especially under the influence of an under-expanded propulsive jet. Strong wall-pressure oscillations occur and can excite detrimental structural vibrations. This study investigates the applicability of convoluted trailing edges/lobe mixers to reduce the separation length and the dynamic loads on a generic axisymmetric launcher model. Experimental investigations were performed at a free-stream Mach number of \(M_{\infty } = 2.9\) and a Reynolds number based on the model diameter of \(Re_D = 1.3 \times 10^6\). A small reduction of the separation length due to the increased turbulent mixing effected by the lobes was observed, and a promising moderating influence on the effects of the jet plume in the low-frequency range could be achieved.
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The German Research Foundation DFG is gratefully acknowledged for financial support within the framework of the SFB TRR40.
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Schreyer, AM., Taskin, G. (2018). Separation Control with Lobe Mixers in the Wake of an Axisymmetric Space-Launcher Model. In: Dillmann, A., et al. New Results in Numerical and Experimental Fluid Mechanics XI. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 136. Springer, Cham. https://doi.org/10.1007/978-3-319-64519-3_29
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DOI: https://doi.org/10.1007/978-3-319-64519-3_29
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