Global visualization of compressible swept convex-corner flow using pressure-sensitive paint

Kung Ming Chung, Yi Xuan Huang

研究成果: Article同行評審

5 引文 斯高帕斯(Scopus)

摘要

This study used pressure-sensitive paint (PSP) and determined the surface pressure distributions for a compressible swept convex-corner flow. The freestream Mach numbers were 0.64 and 0.83. The convex-corner angle and swept angle were, respectively, 10-17° and 5-15°. Expansion and compression near the corner apex were clearly visualized. For the test case of shock-induced boundary layer separation, there were greater spanwise pressure gradient and curved shocks. The acquired PSP data agree with the experimental data measured using the Kulite pressure transducers for a subsonic expansion flow. For a transonic expansion flow, the discrepancy was significant. The assumption of a constant recovery factor is not valid in the separation region, and temperature correction for PSP measurements is required.

原文English
文章編號106
期刊Aerospace
8
發行號4
DOIs
出版狀態Published - 2021 4月

All Science Journal Classification (ASJC) codes

  • 航空工程

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