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• W1976811375 abstract "A numerical investigation was undertaken to evaluate the capabilities of a differential spoiler setting (DSS) in modifying the spanwise wing load and reducing the hazard of wake vortices imposed on a following aircraft. Numerical simulations were carried out on a scaled, half-model aircraft under a high lift configuration (HLC) condition for two outboard loading cases and two inboard loading cases in addition to the baseline configuration case. The study has covered the near-wake field and the extended near-wake field regions. The results are presented in terms of velocity contours, vorticity contours, tangential velocity, circulation, and streamlines at several measurement sections downstream, namely, at x/b=0.345, x/b=0.444, x/b=0.658, x/b=1.794, and x/b=4.484 measured from the wing-tip trailing edge. Comparison between numerical simulations and experimental results has shown good agreement in terms of lift coefficients for all cases and fairly acceptable agreement in terms of maximum cross-flow velocity, maximum normalized total circulation, and maximum-induced rolling moment. However, in some cases the agreement is not good. Evaluation of the results has shown promising outcomes for the inboard loading cases compared with the outboard loading cases, which agree with the experimental results. The interaction between spoilers’ wake and the outboard flap tip vortex of the inboard loading cases reduces the magnitude of the tangential velocity and circulation of the wing tip vortex, delays vortex merging to a farther distance downstream, and thus, minimizes the induced rolling moment imposed on the following aircraft. Therefore, DSS can be considered a promising technique in wake vortex alleviation that can be used commercially in the future. The only limitation of this study is the need for more sophisticated computational resources to benefit from using finer mesh, which can minimize the difference between numerical and experimental results. This should therefore enable extending the study of wake vortices to the very far-wake field or up to a distance where the following aircraft is usually located." @default.
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• W1976811375 date "2015-05-01" @default.
• W1976811375 modified "2023-09-26" @default.
• W1976811375 title "Numerical Study of the Effect of Spoiler Configuration on Wake Vortex Alleviation" @default.
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• W1976811375 doi "https://doi.org/10.1061/(asce)as.1943-5525.0000406" @default.
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