Supersonic separated flow past a cylindrical obstacle on a flat plate

Ozcan O., Holtt M.

AIAA Journal, vol.22, no.5, pp.611-617, 1984 (Scopus) identifier identifier

  • Publication Type: Article / Article
  • Volume: 22 Issue: 5
  • Publication Date: 1984
  • Doi Number: 10.2514/3.48492
  • Journal Name: AIAA Journal
  • Journal Indexes: Scopus
  • Page Numbers: pp.611-617
  • Istanbul Gelisim University Affiliated: No


An experimental investigation of three-dimensional boundary-layer separation on a flat plate ahead of a circular cylinder at Mach 2.36 was made. Emphasis was given given to the laminar flow regime and to the flow region upstream of the cylinder. The heights and diameters of the cylinders used in the study were larger than the undisturbed boundary-layer thickness at the cylinder location. Data were obtained by oil flow visualization, schlieren observations, static pressure measurements, and laser anemometry. Oil flow visualization revealed three separation lines on the flat plate ahead of the cylinder. A postulated flowfield structure, which was suggested by this skin-friction pattern, could not be confirmed by the velocity measurements. Velocity measurements indicated an unsteady flow structure. © 1984 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.