What was learned from the new VFE-2 experiments

Luckring, James M.; Hummel, Dietrich

doi:10.1016/j.ast.2011.07.012

Cited by 27 publications

(12 citation statements)

References 21 publications

(17 reference statements)

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“…The resulting understanding of the flow topology is summarized in Figure 1. 15 Figure 1 showed the pressure sensitive paint and PIV velocity contour together with numerical performed on the VFE-2 configurations. These results were well agreed that the primary vortex will only appear at certain chordwise position on the wing as shown in the figure.…”

Section: Introductionmentioning

confidence: 99%

The effect of edge profile on delta wing flow

Mat

Green

Galbraith

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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Section: Introductionmentioning

confidence: 99%

The effect of edge profile on delta wing flow

Mat

Green

Galbraith

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Within the NATO Research Technology Organization (RTO)/Applied Vehicle Technology (AVT)-113 Task Group, the flow around a 65° delta wing with sharp and round LEs is analyzed by an integrated approach of experimental wind-tunnel tests and numerical simulations. Numerical results using the DLR, German Aerospace Center (DLR) TAU-Code have been described by Schütte and Liideke [9], and summaries of lessons learned are given by Fritz and Cummings [10], as well as by Luckring and Hummel [11]. All resuhs are published in the RTO final report by Lamar and Hummel [12].…”

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confidence: 99%

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Schütte

Hummel

Hitzel³

2012

Journal of Aircraft

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Within the NATO Research and Technology Organisation Applied Vehicle Technology (AVT)-161 task group, titled "Assessment of Stability and Control Predictions for NATO Air and Sea Vehicles," a 53° swept and twisted lambda wing with rounded leading edges is considered. In a first step, the symmetric flow conditions are analyzed in this paper in order to understand the corresponding flow physics. Experiments by the task group are used to develop proper numerical simulation tools for further applications in the design process of unmanned combat aerial vehicles as a part of future air-combat systems. The philosophy of the configuration under consideration is explained. The vortical flowfield is simulated using the DLR, German Aerospace Center TAU-Code applied with different turbulence models on various computational grids. Finally, a best practice is evaluated for medium and large angles of attack. A combination of these numerical results and experimental data lead to a proper understanding of the complex flow structure. Furthermore, this paper addresses the necessity for the predictability and understanding of controlled and uncontrolled flow separation, together with the interaction of the corresponding vortex systems in order to estimate stability and control issues for the entire flight envelope. NomenclatureA = attachment line C¿ = lift coefficient; ¿/(^oo • S) Cl = rolling moment coefficient; l/(q^ • S • c^f) Clß = rolling moment due to sideslip; 9C,/9Ĉ " = pitching moment coefficient (noseup positive); c" = yawing moment coefficient; «/(í/^, • 5-Cref) c"ß = yawing moment due to sideslip; 9C"/9Ĉ p = pressure coefficient; {p -/'oo)/9oo Cf = root chord length of the model cVef = reference length / = frequency /j = moment of inertia around x I y = moment of inertia around y k = reduced frequency; 27r • / • c,^f/VM = Mach number 9tx) = dynamic pressure coefficient; p^ • V^/2 R = Reynolds number; V^ • c^f/v S = reference area 5 = separation line s = half-span Presented a.s

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“…9,11,10 The experimental data adopted in the AG49 work were measured in the Institute of Aerodynamics (AER) of the Technische Universität München (TUM), 16 which was especially directed to the measurements of turbulent flow field and unsteady surface pressure data. The tests were performed for low Reynolds numbers and Mach numbers based on low-speed wind tunnel facilities in TUM, as shown in Figure 1.…”

Section: Experimental Datamentioning

confidence: 99%

“…One of the wellknown studies has been the effort made in the Second International Vortex Flow Experiment (VFE-2) on a 65 • swept delta wing. 6,7,8,9,10,11 The VFE-2 Delta wing has been taken as a test case in many collaborative research project concerning turbulence modelling, due to its intrinsic flow physics of the vortex motions in the form of, among others, vortex formation, interaction, bursting/breakdown and subsequent trailing wake. Unlike with a sharp leading edge, the flow about the VFE-2 delta wing with a rounded leading edge possesses special challenges to represent the flow separation in numerical modelling.…”

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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What was learned from the new VFE-2 experiments

Cited by 27 publications

References 21 publications

The effect of edge profile on delta wing flow

The effect of edge profile on delta wing flow

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

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

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