Boundary-layer stability analysis of the hypersonic international flight research transition experiments

Heath B Johnson, Chris R. Alba, Graham V Candler, Matthew MacLean, Timothy Wadhams, Michael Holden

Research output: Contribution to journalArticlepeer-review

65 Scopus citations


Boundary-layer stability analysis is performed by computational fluid dynamics simulation of experiments conducted in the Calspan-University at Buffalo Research Center Large Energy National Shock Tunnel in support of the first flight of the Hypersonic International Flight Research Experimentation program. From the laminar flow solutions, disturbances are calculated using the linear parabolized stability equations method and instability is quantified by integrating the resulting disturbance growth rates. Comparisons are made between the experimentally measured transition locations and the results of the parabolized stability equations analysis. The results show that for the cases tested, the eN transition correlation works better than the commonly used R/Me engineering criterion for predicting the onset of boundary-layer transition from laminar to turbulent flow.

Original languageEnglish (US)
Pages (from-to)228-236
Number of pages9
JournalJournal of Spacecraft and Rockets
Issue number2
StatePublished - 2008

Bibliographical note

Funding Information:
Work at the University of Minnesota was sponsored by Sandia National Laboratories Award #619327 and by the U. S. Air Force Office of Scientific Research under grant #FA9550-04-1-0341. Work at Calspan–University at Buffalo Research Center was sponsored by the U.S. Army Research Development and Engineering Command under Contract #DAAH01-98-C-R196. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the U.S. Air Force Office of Scientific Research, Aviation and Missile Research, Development, and Engineering Center, or the U.S. Government.


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