Effects of a fillet on the flow past a wing-body junction

Devenport, William J.; Agarwal, Nidhi; Dewitz, Michael B.; Simpson, Roger L.; Poddar, Kamal

doi:10.2514/3.10517

Cited by 59 publications

(8 citation statements)

References 9 publications

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“…The validation of the LES against experimental data, omitted here for brevity but available in [38], shows good agreement for the boundary layer development, wall-pressure contours, shape and magnitude of the vorticity field. Good qualitative agreement for the turbulent kinetic energy is also obtained, but its magnitude is half of that of the experimental data of [2] and the LES data of [39] due to insufficient mesh resolution near the wall. Nevertheless, one can still obtain meaningful information from the comparison of the relative turbulent kinetic energy magnitude between the anti-fairing and the baseline.…”

Section: A Large Eddy Simulationsmentioning

confidence: 65%

“…To align ourselves with the junction flow literature, we choose to simulate a Rood wing instead of a NACA 0015. The flow conditions, shown in Table 1, are the same as in the experiment of Devenport and Simpson [2]. For the simulations, we make use of the in-house finite volume solver INCA, which performs implicit large eddy simulations, whereby the numerical discretization and subgrid-scale model are merged through the discretization of the advective terms based on the adaptive local deconvolution method [34,35].…”

Section: A Large Eddy Simulationsmentioning

confidence: 99%

“…For turbulent flows, the horseshoe vortex system is not steady in terms of location, size, and circulation. In particular, it appears to have an aperiodic bimodal velocity probability distribution [2] which increases the turbulence energy production and turbulent stresses in the junction region by an order of magnitude. Furthermore, the interaction of the wall boundary layer and the one developing on the wing causes high anisotropy levels in the corner region [3] and creates interference effects that tend to increase the drag [4].…”

Section: Introductionmentioning

confidence: 99%

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A Review of Numerical and Experimental Studies of the Anti-Fairing

Belligoli

Dwight

Eitelberg

et al. 2020

Aiaa Aviation 2020 Forum

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An anti-fairing is a concave deformation of the wall around a wing-body junction that can decrease the aerodynamic drag through the activation of a propulsive force generated by the interaction of the curved concave shape and the high-pressure region in proximity of the wing leading-edge. Although this mechanism is well understood, the dynamics of the interaction between the anti-fairing and the junction flow remain largely unexplored. This work brings together all the numerical and experimental studies of the anti-fairing to investigate its effect on turbulent quantities and the robustness of its design to changes to the incoming flow parameters, and to estimate the drag change with respect to a normal wing/flat-plate configuration. It is found that the interaction of the streamwise pressure gradient generated by the anti-fairing with the incoming boundary layer substantially reduces the shear responsible for viscous drag. Furthermore, no significant influence of the incoming boundary layer thickness on the antifairing performance is observed. However, a direct drag measurement with a force balance casts some doubts on the possibility to achieve large drag reductions.

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Section: A Large Eddy Simulationsmentioning

confidence: 65%

Section: A Large Eddy Simulationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A Review of Numerical and Experimental Studies of the Anti-Fairing

Belligoli

Dwight

Eitelberg

et al. 2020

Aiaa Aviation 2020 Forum

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show abstract

“…Efforts to develop methods for the reduction of the size and the strength of the horseshoe vortices have been attempted by various people. Most of them have focused their efforts on the "passive" mechanisms, i.e various nose shapes, such as fillets, swept fairings etc (Kuberdran et al, 1984, Mehta, 1984, Davenport et al, 1989, and wall profiling, such as the ice-formation method (Lafleur and Langston, 1993). The effectiveness -of these methods has been rather limited.…”

Section: Nomenclature •mentioning

confidence: 99%

Experimental Contribution on the Significance and the Control by Transverse Injection of the Horseshoe Vortex

Georgiou

Papavasilopoulos

Alevisos

1996

Volume 1: Turbomachinery

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The present study addresses two aspects of the horseshoe vortex, namely its significance in the secondary flow in a turbine blade passage and the possibility of reducing its strength by an active flow mechanism, i.e the transverse injection of coolant air through a slot in a cylinder-endwall junction. The study reports on the results of two experiments in low speed wind tunnels, which employed a calibrated five-hole Pitot tube to measure the velocity vectors and the resulting secondary flowfields. The first aspect was studied in a 90° square cross section bend duct. The two horseshoe vortex legs were simulated by two half-Delta wing vortex generators. The results showed that the horseshoe vortices influence two regions of the secondary flowfield, i.e one near the passage entrance, where the pressure side leg forces a three dimensional separation of the endwall boundary layer, and the other is in the exit plane, where the coupling of the horseshoe with the passage vortex redistributes the flow with total pressure losses, without affecting the total loss, and increases the secondary kinetic energy by about 20%. For the second aspect, a rectangular bluff body, with a cylindrical leading edge, was positioned over the tunnel endwall and the transverse air injection was implemented through a thin slot, covering the 180° arc in the leading edge-endwall junction. The results showed that, for an average injection velocity equal to 35% that of the mainstream, the size and strength of the horseshoe vortex leg were reduced by nearly 60%. On the other hand, for stronger injection rates the vortex size and strength were increased.

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“…[16] They also made a remark that of attack or varying the approach boundary-layer thickness does not appear to change the qualitative effects of the fillet on the structure of the horseshoe vortex. [3], [5], [14] The experiments done by J.L Fleming stated that the position of maximum velocity directly matches the line of low shear. The flow separation is mainly affected skewing and vortex induced flow near the wall.…”

Section: Grid Generation and Simulation Methodologymentioning

confidence: 99%

CFD Simulation of Flow Past Wing Body Junction: A 3-D Approach

al.¹

2017

IJMPERD

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Turbulence and flow disturbances occurring at the wing body junction of aircraft causes aerodynamic drag and decreases the performance. The main objective of this work is to modify the design at wing body junction by the addition of different types of fillets and strakes and see if there is any reduction from previously generated drag. The validation of the new design was simulated using CFX where Naiver Stokes equations were solved on the modified design by using suitable turbulence models. These small modifications in design proved to be very efficient. Application of these design changes at wing body junction of commercial aircraft will prove to be highly effective in enhancing flight performance.

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Effects of a fillet on the flow past a wing-body junction

Cited by 59 publications

References 9 publications

A Review of Numerical and Experimental Studies of the Anti-Fairing

A Review of Numerical and Experimental Studies of the Anti-Fairing

Experimental Contribution on the Significance and the Control by Transverse Injection of the Horseshoe Vortex

CFD Simulation of Flow Past Wing Body Junction: A 3-D Approach

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