Passive Flow Control for the Load Reduction of Transonic Launcher Afterbodies

Sven Scharnowski, Mickael Bosyk, Ferdinand Schrijer, Bas van Oudheusden

Research output: Contribution to journalArticleScientificpeer-review

4 Citations (Scopus)
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The base flow of an axisymmetric generic space launcher model is investigated experimentally by means of particle image velocimetry and dynamic pressure measurements at a Mach number of 0.76 and a Reynolds number of 1.5 × 106, based on the main body diameter. The flow separation at the end of the main body forms a highly dynamic recirculation region with strong pressure fluctuations on the reattaching surface. The time-averaged reattachment on the rear sting is at 1.05 main body diameters downstream of the step. This work investigates the application of passive flow control devices for their potential of reducing the loads on the space launcher’s nozzle. It is shown that rectangular or circular grooves at the end of the main body force enhanced mixing in the separated shear layer, leading to a reduction of the reattachment length of 55%. Additionally, the fluctuations of the reattachment are significantly reduced, which results in lower-pressure fluctuations and thus reduced dynamic loads.
Original languageEnglish
Pages (from-to)1818-1825
Number of pages8
JournalAIAA Journal: devoted to aerospace research and development
Issue number5
Publication statusPublished - May 2019

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Green Open Access added to TU Delft Institutional Repository ‘You share, we take care!’ – Taverne project
Otherwise as indicated in the copyright section: the publisher is the copyright holder of this work and the author uses the Dutch legislation to make this work public.

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