基于CFD的机翼突风响应计算

doi:CNKI:11-1929/V.20101229.1627.002

Abstract

Abstract: The grid speed method is used to calculate the sharp-edged and 1-cos gust response of wing configuration using computational fluid dynamics (CFD) tools. The spatial discretization of the Euler equations is performed using the central scheme, and time integration was implemented by the dual time-stepping approach. The sharp-edged gust response analysis of both rigid (plunge) and elastic wing configurations is performed, and the acceleration response is calculated and compared with the strip theory results. The 1-cos gust response analysis of rigid (plunge and pitch) wing configuration is performed, and the lift response is calculated and compared with the six degree of freedom (6-DOF) equation results. The results indicate that at low Mach numbers the application of the grid speed method is an effective way to simulate gust responses. At high Mach numbers, however, nonlinear infection is a very important aspect in the simulation of gust response of wing configurations which should be considered in practical applications,while the coupling in 6-DOF equation does not seriously affect the calculated lift history.

Key words: gust response, strip theory, finite volume method, Euler equation, six degree of freedom equation, elastic wing, modal superposition method

CLC Number:

V211.47

GU Ning, LU Zhiliang, ZHANG Jiaqi, GUO Tongqing. CFD-based Analysis for Gust Response of Aircraft Wing[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(5): 785-791.

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CFD-based Analysis for Gust Response of Aircraft Wing

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