Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry

Heather E. Kostak, Rodney D.W. Bowersox, Gregory R. McKiernan, John Thome, Graham V. Candler, Rudolph A. King

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

15 Scopus citations


The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
StatePublished - Jan 1 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: Jan 7 2019Jan 11 2019

Publication series

NameAIAA Scitech 2019 Forum


ConferenceAIAA Scitech Forum, 2019
Country/TerritoryUnited States
CitySan Diego


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