Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge

Fritz, W.

doi:10.1016/j.ast.2012.02.006

Cited by 31 publications

(27 citation statements)

References 21 publications

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“…Further downstream the outer vortex becomes the stronger one, whereas the inner vortex decays. These experimental results are in excellent qualitative agreement with the numerical findings 16 as shown in the right-hand figure. The results of the two campaigns in the Transonic Wind Tunnel at Goettingen in 2004 and 2005 have been summarized 19 and they were also a subject of the 2006 AIAA achievements review 20 as well as to some VFE-2 status reports 21,22 .…”

Section: Introductionsupporting

confidence: 81%

“…8 shows the result for the flow field in various cross-sectional planes for the same free stream conditions as in Fig. 7 and in comparison with the numerical result 16 . The surface pressure distribution from the PSP investigations, see Fig.…”

Section: Introductionmentioning

confidence: 97%

“…After some substantial support by numerical investigations 16 within VFE-2 concerning the technical equipment 7 , 3D PIV investigations 17,18 have been carried out at DLR Goettingen. Fig.…”

Section: Introductionmentioning

confidence: 99%

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What was learned from the new VFE-2 experiments

Luckring

Hummel

2013

Aerospace Science and Technology

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Section: Introductionsupporting

confidence: 81%

Section: Introductionmentioning

confidence: 97%

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What was learned from the new VFE-2 experiments

Luckring

Hummel

2013

Aerospace Science and Technology

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“…The VFE-2 experimental data have been used in a number of previous numerical analysis using different modelling approaches. 12,13,14,15 In the recent GARTEUR AG49 project the VFE-2 delta wing with a rounded leading edge was selected as a test case to verify hybrid RANS-LES modelling in predictions of turbulent flow separation, shear-layer instabilities, as well as the evolution and breakup of coherent vortex structures. ?…”

Section: Introductionmentioning

confidence: 99%

Verification of RANS and Hybrid RANS-LES Modelling in Computations of a Delta-Wing Flow

Peng

2016

46th AIAA Fluid Dynamics Conference

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RANS and hybrid RANS-LES computations were carried out for the flow about the VFE-2 delta wing at a low-speed subsonic Mach number M = 0.14 and an angle of attack α = 23 • . In the hybrid RANS-LES computation an algebraic zero-equation model was invoked, and the RANS computations were conducted with, respectively, the SpalartAllmaras (SA) model and an Explicit Algebraic Reynolds Stress Model (EARSM) based on k − ω formulation. The modelling performance in simulating the vortical flow was verified by means of comparative analysis and in comparison with available experimental measurements. The vortex bursting phenomenon, observed in the experiment at α = 23 • , was confirmed in the present hybrid RANS-LES computation, which has further highlighted the spiraling motion preceding to the vortex bursting. All models have claimed a topology of the vortex system that is similar to the experimental oil visualization. The hybrid RANS-LES computation has reproduced the mean flow in a more reasonable pattern than the RANS computation, in view of the resolved secondary vortex and the predicted surface pressure that is in much better agreement with the experiment. It is shown that, for resolving turbulence, the so-called "grey-area" problem becomes rather severe in the hybrid RANS-LES computation, which has, in the initial stage of vortex formation and evolution, under-resolved significantly the turbulent fluctuations of the vortical flow and, when approaching the trailing edge, over-predicting the surface pressure fluctuations.

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“…The profile of the model [7] is shown in Figure 1(a) and its installation in the wind tunnel is shown in Figure 1(b). The results from this campaign were compared with each other and with the CFD codes [14]. More experiments are needed in the future to investigate the boundary layer status and the behaviours of the vortex breakdown across the wing.…”

Section: Introductionmentioning

confidence: 99%

Development of Delta Wing Aerodynamics Research in Universiti Teknologi Malaysia Low Speed Wind Tunnel

Mat

Ishak

Lazim

et al. 2014

Advances in Mechanical Engineering

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This paper presents wind tunnel experiment on two delta wing configurations which are differentiated by their leading edge profiles: sharp and round-edged wings. The experiments were performed as a part of the delta wing aerodynamics research development in Universiti Teknologi Malaysia, low speed tunnel (UTM-LST). Steady load balance and flow visualization tests were conducted at Reynolds numbers of 0.5, 1, and 1.5 × 10 6 , respectively. The flow measurement at low Reynolds number was also performed at as low as speed of 5 m/s. During the experiments, laser with smoke flow visualizations test was performed on both wings. The study has identified interesting features of the interrelationship between the conventional leading edge primary vortex and the occurrence and development of the vortex breakdown above the delta wings. The results conclude the vortex characteristics are largely dependent on the Reynolds number, angle of attack, and leading-edge radii of the wing.

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Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge

Cited by 31 publications

References 21 publications

What was learned from the new VFE-2 experiments

What was learned from the new VFE-2 experiments

Verification of RANS and Hybrid RANS-LES Modelling in Computations of a Delta-Wing Flow

Development of Delta Wing Aerodynamics Research in Universiti Teknologi Malaysia Low Speed Wind Tunnel

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