Maximilian Karsch, Jeroen Van den Eynde & Johan Steelant

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-340

The transition from laminar to turbulent flow in a hypersonic boundary layer is modelled using an
intermittency­based linear combination approach. A simplified transition model like this enables a quick
assessment of aero­thermal loads and the overall flight efficiency of high­speed vehicles during the initial design phase by weighting purely laminar and turbulent flow results on the basis of an empirically
calculated intermittency. The transition model presented within this work includes an empirical model
to account for Mach number, Reynolds number, wall temperature and pressure gradient effects on turbulent spot growth based on available turbulent spot studies in literature. A validation of the transition
model is carried out for a number of different test cases and a methodology to extend the model to
generic geometries is presented to enable a more general application.

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In Categories: 1.Events, HiSST 2022, Hypersonic Fundamentals and History
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