SEPARATED FLOW AROUND A FLAT-NOSED CIRCULAR-CYLINDER AT ZERO ANGLE-OF-ATTACK


ACAR H., ILDAY O., ELBAY M., ATLI V.

RECHERCHE AEROSPATIALE, ss.55-62, 1993 (SCI İndekslerine Giren Dergi) identifier

  • Basım Tarihi: 1993
  • Dergi Adı: RECHERCHE AEROSPATIALE
  • Sayfa Sayıları: ss.55-62

Özet

The separated flow around a flat-nosed circular cylinder at zero angle of attack was experimentally investigated at low subsonic velocity. First, the effect of the aspect ratio, I/d, of the cylinder (base flow influence) on the separated flow around the nose was investigated using the surface flow visualization technique and performing surface pressure measurements. Mean velocity and turbulence measurements were made by hot-wire probe 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, referenced to the cylinder diameter: Re(d) = 3.45 x 10(4), 5.18 x 10(4), 7.59 x 10(4).