Using computational fluid dynamics method, numerical simulation is carried out on the typical two-dimensional multi-segment wing with the deflection hinged flap configuration of spoiler, and the influence of the down-deflection of the spoiler on the Reynold number effect of the multi-segment wing is studied. the result show that: Within the scope of this article, 1) The camber effect produced by the deflection of spoiler can increase lift at small angles of attack but has a limited effect on the CL-MAX; 2) The spoiler down-deflection configuration has a limited affection of Reynold number in linear segment, which is more affected near stall, the slope of CL is affected by Reynold number.
Eight different height-to-length ratio forward-facing steps are investigated in this paper to study the tolerance of steps on leading edge of the main wing of an aircraft during landing. Numerical simulation is applied to simulate the separation and subsequent vortex formation around a multi-element airfoil with various steps. Aerodynamic characteristics of different steps show that steps with H/L ratio less than 1/4 turn out to have less effect on aerodynamic performance of an aircraft. Inclined plane can be applied to the trailing edge of the slat during high lift devices design.
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