Steady, subsonic CFD analysis of the VFE-2 configuration and comparison to wind tunnel data
2008 (English)In: 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008Conference paper (Refereed)
A steady computational fluid dynamic (CFD) study is performed over a wide range of Reynolds numbers at low incidence and subsonic speeds on the Second International Vortex Flow Experiment (VFE-2) blunt leading-edge delta wing of 65° sweep. The numerical results are presented and compared to experimental data and are further used to understand the formation of a weak, thin vortical structure that develops upstream of primary leading-edge separation onset. Comparisons between computational results and experiments are presented with regard to surface pressure coefficient and surface flow patterns for the suction side of the delta wing. Inviscid computations displaying a similar vortical pattern as the viscous results raise the doubt that time-accurate computations might be necessary to correctly predict the formation of the weak apex vortex.
Place, publisher, year, edition, pages
CFD analysis, Computational results, Delta wings, Experimental data, Flow experiments, Leading edge, Numerical results, Subsonic speed, Suction side, Surface flow patterns, Surface pressure coefficients, Time-accurate, Vortical structures, Wind-tunnel data
IdentifiersURN: urn:nbn:se:kth:diva-8478ScopusID: 2-s2.0-78149456322ISBN: 9781563479373OAI: oai:DiVA.org:kth-8478DiVA: diva2:13813
46th AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV; United States; 7 January 2008 through 10 January 2008
QC 201007132008-05-162008-05-162014-10-13Bibliographically approved