ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Dynamic stall control of rotor airfoil via trailing-edge flap
Received date: 2016-04-11
Revised date: 2016-07-16
Online published: 2016-08-02
Supported by
National Natural Science Foundation of China (11272150, 11572156); Jiangsu Innovation Program for Graduate Education (KYLX15_0244); Priority Academic Program Development of Jiangsu Higher Education Institutions
Control effects of typical motion parameters of trailing-edge flap (TEF) on the dynamic stall characteristics of rotor airfoil are investigated. A high-efficiency and high-precision CFD method for predicting the unsteady flow characteristics of rotor airfoil with TEF control is developed. The viscous and orthogonal body-fitted grids around the oscillatory rotor airfoil are regenerated by solving Poisson equations. To ensure the quality of the grids around TEF, a reconstruction of grid points on airfoil is conducted to describe the motion of TEF. Aiming at overcoming the shortcoming of deformable grid approach, which may result in the distortion of grid, a moving-embedded grid method is developed to predict the flowfield of the oscillatory airfoil with TEF control. Based on unsteady Reynolds averaged Navier-Stokes (URANS) equations, dual-time method, Spalart-Allmaras (S-A) turbulence model, and Roe-Monotone Upwind-centered Scheme for Conservation Laws (Roe-MUSCL) scheme, a high-precision CFD method for predicting the flowfield around airfoil is developed, and implicit Lower-Upper Symmetric Gauss-Seidel (LU-SGS) scheme and parallel techniques are adopted to improve computational efficiency. The dynamic stall cases of HH-02 and SC1095 rotor airfoils are calculated using the proposed method. It is demonstrated that the hysteresis effects are well captured, verifying the effectiveness of numerical simulation method. Focusing on the dynamic stall cases of SC1095 rotor airfoil, analyses on dynamic stall control via TEF are carried out. The function Po and Pc which can reflect the lift, drag and moment characteristics of airfoil are proposed. The effects of the non-dimensional frequency, the phase difference and the angular amplitude of the trailing-edge flap are revealed. The results indicate that dynamic stall phenomenon of an oscillatory airfoil could be significantly suppressed when relative motion frequency of the trailing-edge flap is 1.0 and the phase difference is about 0°. At this state, the maximum drag and negative moment coefficients of SC1095 airfoil can be reduced by about 19% and 27% respectively via TEF control when the angular amplitude is 10°.
MA Yiyang , ZHAO Qijun , ZHAO Guoqing . Dynamic stall control of rotor airfoil via trailing-edge flap[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(3) : 120312 -120312 . DOI: 10.7527/S1000-6893.2016.0220
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