Abstract
Scale resolving numerical methods are necessary to accurately predict the afterbody flows of space launchers. Numerical workflows built for such computations have to be designed in order to obtain a minimal numerical dissipation to resolve fine turbulent structures, a sufficient robustness to capture eventual shock waves and both a reasonable computational cost and an acceptable user workload enabling comparative design studies. This article presents the development of a hybrid numerical framework based on Ducros’s sensor and designed to switch from a low-dissipation formulation in presence of vortical structures to a robust formulation around high gradients. This hybrid workflow is used with ZDES, including its latest automatic mode (ZDES mode 2 (2020)), to simulate a transonic space launcher afterbody experiment with and without a cold air propulsive jet [1,2]. The salient physical properties of the base flow are investigated and the evaluation of computed results follows the extended nomenclature for validation of simulation techniques [3] from level 0 to 5. The framework is thus validated for instantaneous and mean flow visualizations, base and extension mean pressure coefficient distribution, pressure fluctuation levels, one-point and two-point spectral analyses. Such an efficient automatic RANS/LES strategy could be well suited to study realistic launcher afterbody geometries with propulsive jet(s).
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