Direct numerical simulations of hypersonic boundary-layer transition for a slender cone

Christoph Hader, Madlen Leinemann, Hermann F. Fasel

Research output: Chapter in Book/Report/Conference proceedingConference contribution


Direct Numerical Simulations (DNS) were carried out to investigate the laminar-turbulent transition process for a slender (2.5 half-angle) straight (right) cone at Mach 6 and zero angle of attack. The slender cone geometry of the experiments in the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used for the numerical investigations. The simulation results indicate that the so-called fundamental breakdown was the dominant nonlinear mechanism in the downstream part of the slender cone geometry where “hot” streaks have recently been observed in the BAM6QT experiments. Contours of the time-averaged Stanton number obtained from DNS also exhibited the formation of “hot” streaks similar to the ones detected in the experiments. The results for the slender cone provide additional evidence that the laminar turbulent transition process and the associated “hot” streak development for the “quiet” flow conditions in the BAM6QT facility is dominated by the fundamental breakdown mechanism.

Original languageEnglish (US)
Title of host publicationAIAA AVIATION 2020 FORUM
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105982
StatePublished - 2020
EventAIAA AVIATION 2020 FORUM - Virtual, Online
Duration: Jun 15 2020Jun 19 2020

Publication series

Volume1 PartF


CityVirtual, Online

ASJC Scopus subject areas

  • Nuclear Energy and Engineering
  • Aerospace Engineering
  • Energy Engineering and Power Technology

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