Decollement autour d'un cylindre circulaire a nez plat place a incidence nulle

Translated title of the contribution: Separated flow around a blunt-nosed circular cylinder at zero angle of attack

H. Acar*, O. Ilday, M. K. Elbay, V. Atli

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

1 Citation (Scopus)

Abstract

The separated flow around a blunt-nosed circular cylinder at zero angle of attack was experimentally investigated at a low subsonic velocity. First, the effect of the slenderness ratio, I/d, of the cylinder (base flow influence) on the separated flow around the nose was investigated by using the surface flow visualization technique and performing surface pressure measurements. Then mean velocity and turbulence measurements were made by employing the hot-wire technique, in order to investigate the axisymmetric separated flow around the nose in the case of I/d = 7.5, where the base flow has no effect on the nose region. These hot-wire measurements were carried out at three different Reynolds numbers, based on the cylinder diameter: Red=3.45×104, 5.18×104, and 7. 59×104.

Translated title of the contributionSeparated flow around a blunt-nosed circular cylinder at zero angle of attack
Original languageFrench
Pages (from-to)55-62
Number of pages8
JournalRecherche aerospatiale
Issue number3
Publication statusPublished - May 1993

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