Direct Numerical Simulation of a turbulent spot in a cone boundary-layer at Mach 6

Jayahar Sivasubramanian, Hermann F. Fasel

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

19 Scopus citations


Highly resolved spatial Direct Numerical Simulations (DNS) were performed to investigate the growth and breakdown of a localized disturbance into a turbulent spot in a sharp cone boundary - layer at Mach 6. The flow parameters used in the simulations are based on the experimental conditions of the Boeing/AFOSR Mach 6 quiet - flow Ludwieg Tube at Purdue University.1 In order to model a natural transition scenario, the boundary - layer was pulsed through a hole on the cone surface. The pulse disturbance developed into a three-dimensional wave packet which consisted of a wide range of disturbance frequencies and wave numbers. The dominant waves within the resulting wave packet were identified as two - dimensional second mode disturbance waves. In addition, weaker oblique waves were observed on the lateral sides of the wave packet. The developing wave packet grows linearly at first before reaching the nonlinear regime and eventually leads to localized patches of turbulent flow (turbulent spot). The wall - pressure disturbance spectrum showed strong secondary peaks at the fundamental frequency for larger azimuthal wave numbers. This development indicates that fundamental resonance might be the dominant nonlinear mechanism for a cone boundary - layer at Mach 6. The flow structures within the turbulent spot were studied in detail and general features of the spot were analyzed.

Original languageEnglish (US)
Title of host publication40th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781617389221
StatePublished - 2010

Publication series

Name40th AIAA Fluid Dynamics Conference

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes


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