A computational study of laminar-flow secondary separation on a slender delta wing. (12th September 2018)

• Record Type: Journal Article
• Authors: Jones, I. P.; Riley, N.
• Is Part Of: Aeronautical journal. Volume 122:Number 1256(2018)
• Page Start: 1654
• Page End: 1672
• Publication Date: 2018-09-12
• Subjects: Delta wings, -- leading edge vortices, -- secondary flow separation, -- vortex sheets, -- computational fluid dynamics, -- laminar flow, -- validation; Aeronautics -- Periodicals; 629.1305
• DOI: 10.1017/aer.2018.92
• Languages: English
• ISSNs: 0001-9240

Abstract

ABSTRACT: The laminar flow over a slender delta wing at incidence has been extensively studied both experimentally and theoretically using vortex sheet methods. These vortex sheet methods have generally been successful apart from the prediction of the secondary boundary-layer separation induced by the primary vortex. This paper revisits the problem using computational fluid dynamics (CFD) and focusses on the effects of the secondary flow separation. The modelling approach is briefly summarised, and the results are compared with flow measurements and results from vortex sheet methods. The computations show very good agreement with measurements for the surface pressures and total head contours. The results help to understand the complex structure of the leading edge vortex flow, and the associated secondary separation of the boundary layer. They indicate that inviscid mechanisms dominate the larger scale features, and highlight a possible mechanism for the development of an instability in the leading edge vortex sheet.