大型客机增升构型缝翼除冰状态失速特性

doi:10.7527/S1000-6893.2022.27077

Abstract

Abstract:

Under the working condition of the anti-icing/de-icing system， the influence of residual ice on the stall performance of aircraft is the direct basis for evaluating whether the system efficiency meets the design standard. Aiming at the protection scheme of the outboard wing for a high-lift configuration of large civil aircraft， we compare the stall and separation characteristics under the conditions of slat without icing/icing/de-icing with the numerical simulation method. Despite the reduction of the protection area scheme of outboard wing for a high-lift configuration compared with similar civil aircraft， the current scheme can still keep the separation pattern occurring from inboard， ensure the longitudinal moment stability near the critical angle of attack， and effectively expand the stall boundary. The aerodynamic basis for canceling the local protection is the inherent comprehensive effect of downwash and spanwise flow outside the nacelle， which will weaken the impact of the angle of attack and inhibit the flow separation induced by local icing. The conclusions of this paper provide a theoretical basis for the design optimization of protection area and the icing certification of large civil aircraft.

Key words: large civil aircraft, ice, high-lift configuration, slat, anti-icing/de-icing, stall performance

CLC Number:

V211.4

Xiong HUANG, Shiru QU, Heng ZHANG, Xiantiao CHEN. Stall performance of high-lift configuration of large civil aircraft with slat de-icing[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(1): 627077.

Figures/Tables 17

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Stall performance of high-lift configuration of large civil aircraft with slat de-icing

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