Transition of subsonic and transonic expansion-corner flows

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A naturally developed turbulent boundary layer past convex corners was studied. Attention is on the transition of subsonic and transonic expansion flows. Convex-corner angle α ranges from 5 to 20 deg, and freestream Mach numbers M are 0.33, 0.64, and 0.83. Reynolds numbers based on the incoming boundary-layer thickness Reδ0 are 10.0, 14.9, and 16.8 × 104, respectively. Transition of subsonic and transonic expansion-corner flow is observed at M2 α = 6.14. The sudden expansion near the corner is also scaled with this parameter at M = 0.64 and 0.83, but not for M = 0.33.

Original languageEnglish
Pages (from-to)1079-1082
Number of pages4
JournalJournal of Aircraft
Issue number6
Publication statusPublished - 2000 Jan 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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