Numerical investigation of shock-induced laminar separation bubble in supersonic flows

Jayahar Sivasubramanian, Hermann F Fasel

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

3 Scopus citations

Abstract

A numerical study of the interaction between an impinging oblique shock-wave and a laminar boundary-layer on a flat plate is carried out to investigate the resulting twodimensional separation bubble at a freestream Mach number of 2.0 for the approach flow. The flow parameters used for the present investigation matches the laboratory conditions in the experiments conducted by Hakkinen et al.1 The skin friction and pressure distribution from the simulation are compared to the experimental and numerical results available in the literature. The results also confirm the asymmetric nature of the separation bubble reported in the literature. In addition, the development of low-amplitude disturbances is investigated to study the linear stability of the laminar separation bubble. Furthermore, the effects of increased shock incidence angle and Reynolds number are also investigated.

Original languageEnglish (US)
Title of host publication45th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103629
StatePublished - 2015
Event45th AIAA Fluid Dynamics Conference, 2015 - Dallas, United States
Duration: Jun 22 2015Jun 26 2015

Other

Other45th AIAA Fluid Dynamics Conference, 2015
CountryUnited States
CityDallas
Period6/22/156/26/15

ASJC Scopus subject areas

  • Engineering (miscellaneous)
  • Aerospace Engineering

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    Sivasubramanian, J., & Fasel, H. F. (2015). Numerical investigation of shock-induced laminar separation bubble in supersonic flows. In 45th AIAA Fluid Dynamics Conference American Institute of Aeronautics and Astronautics Inc, AIAA.