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Delayed detached eddy simulations of fighter aircraft at high angle of attack

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Abstract

The massively separated flows over a realistic aircraft configuration at 40\(^{\circ }\), 50\(^{\circ }\), and 60\(^{\circ }\) angles of attack are studied using the delayed detached eddy simulation (DDES). The calculations are carried out at experimental conditions corresponding to a mean aerodynamic chord-based Reynolds number of \(8.93\times 10^{5}\) and Mach number of 0.088. The influence of the grid size is investigated using two grids, \(20.0\times 10^{6}\) cells and \(31.0\times 10^{6}\) cells. At the selected conditions, the lift, drag, and pitching moment from DDES predictions agree with the experimental data better than that from the Reynolds-averaged Navier–Stokes. The effect of angle of attack on the flow structure over the general aircraft is also studied, and it is found that the dominated frequency associated with the vortex shedding process decreases with increasing angle of attack.

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Acknowledgments

This paper was supported by National Natural Science Foundation of China (Grant 11302245). The authors have been benefited from discussions with Prof. Song Fu and Associated Prof. Zhixiang Xiao of Tsinghua University. Dr. Zhitao Liu and Dr. Haiyou Zhang provided the experimental data and discussions.

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  1. China Aerodynamics Research and Development Center, Mianyang, 621000, China

    Guoliang Xu, Xiong Jiang & Gang Liu

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  1. Guoliang Xu
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  2. Xiong Jiang
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  3. Gang Liu
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Correspondence to Guoliang Xu.

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Xu, G., Jiang, X. & Liu, G. Delayed detached eddy simulations of fighter aircraft at high angle of attack. Acta Mech. Sin. 32, 588–603 (2016). https://doi.org/10.1007/s10409-016-0565-3

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  • DOI: https://doi.org/10.1007/s10409-016-0565-3

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