Hypersonic three-dimensional boundary layer transition on a cone at angle of attack

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

3 Scopus citations

Abstract

The process of transition in three-dimensional hypersonic boundary layers is highly complex. For a cone at angle of attack, first mode, second mode, and crossflow instabilities are commonly present and can contribute to laminar breakdown. Based on recent experiments conducted in the Purdue Boeing/AFOSR Mach 6 quiet tunnel, two direct numerical simulations of a 7.0° half angle sharp cone in Mach 6 flow at an angle of attack of 6.0° were completed in order gain further insight into the transition process. These simulations were generated on appropriately resolved grids using a high-order, low-dissipation scheme that has been developed at the University of Minnesota and incorporated into the computational fluid dynamics solver US3D. Comparisons of the experimental observations were made with the direct numerical simulations.

Original languageEnglish (US)
Title of host publication41st AIAA Fluid Dynamics Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781600869471
DOIs
StatePublished - 2011
Event41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States
Duration: Jun 27 2011Jun 30 2011

Publication series

Name41st AIAA Fluid Dynamics Conference and Exhibit

Conference

Conference41st AIAA Fluid Dynamics Conference and Exhibit 2011
CountryUnited States
CityHonolulu, HI
Period6/27/116/30/11

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