Visualization of supersonic boundary-layer transition on a 10-degree cone model using temperature-sensitive paint

Yasuhiro Egami, Yoshimi Iijima, Keisuke Asai

Research output: Contribution to journalArticle

Abstract

A boundary layer transition on a 10-degree cone model in a supersonic flow was visualized by means of a temperature-sensitive paint (TSP). A transition front can be detected as the edge of brightness measuring the temperature difference between laminar and turbulent boundary layers. To enhance a thermal signature across the transition line, a sudden temperature step is introduced into the wind tunnel and global transition patterns on the cone model were clearly visualized. In this study, a quiet test region in the test section was visualized first. Then, the effects of Mach numbers, Reynolds numbers and angles of attack on the transition patterns were studied with emphasis on transition caused by crossflow instability.

Original languageEnglish
Pages (from-to)259-265
Number of pages7
JournalNihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B
Volume76
Issue number762
DOIs
Publication statusPublished - 2010 Feb
Externally publishedYes

Keywords

  • Boundar layer transition
  • Cone model
  • Crossflow instability
  • Quiet test region
  • Supersonic flow
  • Temperature-sensitive paint
  • Visualization

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Mechanical Engineering

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