Numerical investigation of Reynolds number effects on a blunt leading-edge delta wing
2006 (English)In: 24th AIAA Applied Aerodynamics Conference: San Francisco, CA : 5 June 2006 through 8 June 2006, 2006, 708-726 p.Conference paper (Refereed)
Numerical results are presented and discussed in this paper allowing a deeper and more precise characterization of the unique double vortex system, which develops on the second International Vortex Flow Experiment (VFE-2) blunt leading edge delta wing of 65° sweep. Computational fluid dynamic (CFD) computations have been performed for three Reynolds numbers (2, 6 and 60 million) at three angles of attack (13.3°, 18.5° and 23.0°) for a fixed Mach number of 0.4. Leading edge primary separation onset is shown to match best the available wind tunnel data at the highest investigated Reynolds number of 60 million and at an angle of attack of 23.0°. At this condition, the coupling between outer primary vortex attachment line with the inner primary vortex separation line is clearly recognizable. Only if the inner primary vortex strength is predicted well, the attached flow passing under the inner primary vortex core is accelerated sufficiently to trigger (inner) secondary separation.
Place, publisher, year, edition, pages
2006. 708-726 p.
, Collection of Technical Papers : AIAA Applied Aerodynamics Conference, ISSN 1048-5953
Angle measurement; Computational fluid dynamics; Delta wing aircraft; Numerical methods; Vortex flow; Wind tunnels; Mach numbers; Secondary separation; Vortex strength
IdentifiersURN: urn:nbn:se:kth:diva-8476ScopusID: 2-s2.0-33845409766ISBN: 978-156347812-3OAI: oai:DiVA.org:kth-8476DiVA: diva2:13811
QC 201007132008-05-162008-05-162010-07-13Bibliographically approved