Open-type separation on delta wings for leading-edge bluntness

Kazuhisa Chiba, Shigeru Obayash, Kazuhiro Nakahash

Research output: Contribution to journalArticlepeer-review

Abstract

A numerical simulation was carried out corresponding to recent experiments using delta wings with sharp and blunt leading-edges, which indicates the second primary vortex, at NASA Langley Research Center. However, the experimental data did not reveal the detailed physical phenomena regarding the second primary vortex, because the experiment used only on-the-body-surface data. In the present study, the physical phenomena were revealed using Reynoldsaveraged Navier-Stokes computations with three one-equation turbulence models on an unstructured hybrid mesh. The adaptive mesh refinement method in the vicinity of the vortex center was also applied to have more mesh resolution. Consequently, the result quantitatively revealed that appropriate modeling regarding turbulent kinematic viscosity was significant. Moreover, the three-dimensional visualization of the computational fluid dynamics results suggested that the second primary vortex was a developing shear layer merging into an open-type separation generated late by the primary vortex.

Original languageEnglish
Pages (from-to)81-87
Number of pages7
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Volume50
Issue number168
DOIs
Publication statusPublished - 2007

Keywords

  • Bluntness effect
  • Delta wing
  • Leading-edge separation
  • Open-type separation

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Fingerprint Dive into the research topics of 'Open-type separation on delta wings for leading-edge bluntness'. Together they form a unique fingerprint.

Cite this