Separated flow around a blunt-nosed circular cylinder at zero angle of attack,Decollement autour d'un cylindre circulaire a nez plat place a incidence nulle

Acar H., Ilday Ö., Elbay M., Atli V.

RECHERCHE AEROSPATIALE, no.Issue 3, pp.55-62, 1993 (Scopus) identifier

  • Publication Type: Article / Article
  • Publication Date: 1993
  • Journal Indexes: Scopus
  • Page Numbers: pp.55-62
  • Istanbul Medipol University Affiliated: No


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.