Potential flow solutions with wakes over an ogive cylinder

Tuncer İ. H., Platzer M.

JOURNAL OF SPACECRAFT AND ROCKETS, vol.35, no.3, pp.273-277, 1998 (SCI-Expanded, Scopus) identifier identifier

  • Publication Type: Article / Article
  • Volume: 35 Issue: 3
  • Publication Date: 1998
  • Doi Number: 10.2514/2.3351
  • Journal Name: JOURNAL OF SPACECRAFT AND ROCKETS
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Page Numbers: pp.273-277
  • Middle East Technical University Affiliated: Yes

Abstract

An incompressible panel code is employed to compute the flow over an ogive cylinder body with an overall length of 7.5 diameter. Flow separation is modeled by vortex wakes attached to the base region and the leeward sides of the cylinder body. The computed surface pressures and integrated normal force and pitching-moment coefficients are found to be in good agreement with the experimental data up to 20-deg incidence. This favorable agreement suggests that the panel codes may be a computationally efficient tool in the aerodynamic missile design process at low incidences.