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Steady, subsonic CFD analysis of the VFE-2 configuration and comparison to wind tunnel data
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2008 (English)In: 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008Conference paper, Published paper (Refereed)
Abstract [en]

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
2008.
Keyword [en]
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
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-8478Scopus ID: 2-s2.0-78149456322ISBN: 9781563479373 (print)OAI: oai:DiVA.org:kth-8478DiVA: diva2:13813
Conference
46th AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV; United States; 7 January 2008 through 10 January 2008
Note

QC 20100713

Available from: 2008-05-16 Created: 2008-05-16 Last updated: 2014-10-13Bibliographically 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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