Transactions of Nanjing University of Aeronautics & Astronautics
Numerical Investigations on Dynamic Stall Characteristics of a Finite Wing
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Abstract:
The paper examines the dynamic stall characteristics of a finite wing with an aspect ratio of eight in order to explore the 3D effects on flow topology， aerodynamic characteristics， and pitching damping. Firstly， CFD methods are developed to calculate the aerodynamic characteristics of wings. The URANS equations are solved using a finite volume method， and the two-equation k-ω shear stress transport （SST） turbulence model is employed to account for viscosity effects. Secondly， the CFD methods are used to simulate the aerodynamic characteristics of both a static， rectangular wing and a pitching， tapered wing to verify their effectiveness and accuracy. The numerical results show good agreement with experimental data. Subsequently， the static and dynamic characteristics of the finite wing are computed and discussed. The results reveal significant 3D flow structures during both static and dynamic stalls， including wing tip vortices， arch vortices， Ω-type vortices， and ring vortices. These phenomena lead to differences in the aerodynamic characteristics of the finite wing compared with a 2D airfoil. Specifically， the finite wing has a smaller lift slope during attached-flow stages， higher stall angles， and more gradual stall behavior. Flow separation initially occurs in the middle spanwise section and gradually spreads to both ends. Regarding aerodynamic damping， the inboard sections mainly generate unstable loading. Furthermore， sections experiencing light stall have a higher tendency to produce negative damping compared with sections experiencing deep dynamic stall.
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Project Supported:
This work was supported by the National Natural Science Foundation of China （No.12072156）， the National Key Laboratory Foundation of China （No.61422202103）， and the Priority Academic Program Development of Jiangsu Higher Education Institutions （PAPD）.
Clc Number:
V212.4
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