Fluorescence visualization of hypersonic flow establishment over a blunt fin

J. S. Fox, S. O’Byrne, A. F.P. Houwing, A. Papinniemi, P. M. Danehy, N. R. Mudford

Research output: Contribution to journalArticlepeer-review

20 Citations (Scopus)

Abstract

Fluorescence imaging is used to investigate the separated flow upstream of a blunt fin in a hypersonic freestream with a transitional boundary layer. Images are presented to show the flow development before, during, and after the test time of the free-piston shock tunnel used to generate the flow. These images indicate that the test time in this facility is long enough to achieve a steady flow over the blunt fin. Thermocouple measurements are included to compare the surface heat flux upstream of the fin with that for flow along a flat plate with the same freestream conditions. The heat flux results are consistent with separation in a transitional boundary layer and show that the separated flow is oscillatory.

Original languageEnglish
Pages (from-to)1329-1337
Number of pages9
JournalAIAA Journal
Volume39
Issue number7
DOIs
Publication statusPublished - Jul 2001

Fingerprint

Dive into the research topics of 'Fluorescence visualization of hypersonic flow establishment over a blunt fin'. Together they form a unique fingerprint.

Cite this