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Initial steady/unsteady CFD analysis of vortex flow over the VFE-2 delta wing
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2006 (English)In: 25th Congress of the International Council of the Aeronautical Sciences, 3-8 September 2006, Hamburg, Germany, 2006, 883-892 p.Conference paper, Published paper (Refereed)
Abstract [en]

This study is aimed at assessing the application of the latest unstationary CFD method, Detached- Eddy Simulation (DES), to simulate the flowfield around blunt leading edge delta wings. For this purpose, the Second International Vortex Flow Experiment (VFE-2) 65° sweep delta wing model was used to perform numerical investigations at a Reynolds number of 6 million, Mach number of 0.4 and angles of attack of 18.5° and 23°. As the nature of this study is mainly exploratory, various numerical grids have been used. The results confirm the maturity of Reynolds averaged Navier-Stokes (RANS) methods but also the problems of DES to predict free separation and the grid sensitivity of this model.

Place, publisher, year, edition, pages
2006. 883-892 p.
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-8477Scopus ID: 2-s2.0-84878435922ISBN: 978-160423227-1 (print)OAI: oai:DiVA.org:kth-8477DiVA: diva2:13812
Conference
25th Congress of the International Council of the Aeronautical Sciences 2006; Hamburg; Germany
Note

QC 20100713

Available from: 2008-05-16 Created: 2008-05-16 Last updated: 2014-10-30Bibliographically approved
In thesis
1. Advances in vortical flow prediction methods for design of delta-winged aircraft
Open this publication in new window or tab >>Advances in vortical flow prediction methods for design of delta-winged aircraft
2008 (English)Doctoral thesis, comprehensive summary (Other scientific)
Abstract [en]

This thesis covers the field of vortex-flow dominated external aerodynamics. As part of the contribution to the AVT-113 task group it was possible to prove the feasibility of high Reynolds number CFD computations to resolve and thus better understand the peculiar dual vortex system encountered on the VFE-2 blunt leading edge delta wing at low to moderate incidences. Initial investigations into this phenomenon seemed to undermine the hypothesis, that the formation of the inner vortex system depends on the laminar/turbulent state of the boundary layer at separation onset. As a result of this research, the initial hypothesis had to be expanded to account also for high Reynolds number cases, where a laminar boundary layer at separation onset can be excluded.

In addition, unsteady transonic computations are used to shed light on a highly non-linear phenomenon encountered at high angles of incidence. At certain conditions, the increase of the incidence by a single degree leads to a sudden movement of the vortex breakdown location from the trailing edge to mid-chord.

The lessons learned from the contribution to the VFE-2 facet are furthermore used to prove the technology readiness level of the tools within the second facet of AVT-113, the Cranked Arrow Wing Aerodynamics Project International (CAWAPI). The platform for this investigation, the F-16XL aircraft, experiences at high transonic speeds and low incidence a complex interaction between the leading edge vortex and a strong, mid-chord shock wave.

A synergetic effect of VFE-2 with a further project, the Environmentally friendly High Speed Aircraft (HISAC), is also presented in this thesis. Reynolds number dependence is documented in respect to leading edge vortex formation of the wing planform for a reference HISAC configuration. Furthermore, proof is found for a similar dual vortex system as for the VFE-2 blunt leading edge configuration.

Place, publisher, year, edition, pages
Stockholm: KTH, 2008. viii, 38 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2008:30
Keyword
delta wing, slender wing, aircraft, vortex, VFE-2, CAWAPI, HISAC
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-4761 (URN)978-91-7178-970-9 (ISBN)
Public defence
2008-06-09, F3, KTH, Lindstedtsvägen 26, Stockholm, 10:15
Opponent
Supervisors
Note
QC 20100713Available from: 2008-05-16 Created: 2008-05-16 Last updated: 2010-07-13Bibliographically approved

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