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摘要
The effects of wind tunnel sidewalls on the airfoils were studied in this paper by experimental method and numerical simulation. The experiment was carried out in IET low-speed wind tunnel and the surface pressure was measured. Blunt airfoils is DU91-W2-250_6, DU91-W2-250_6 and DU91-W2-250_10. The Reynolds number is 2.62×105 based on the tunnel size and wind speed available. Simulation was done with RANS method and SST-transition model for turbulence. The domain and boundary condition for calculation were set basically to model the experiment. For the baseline airfoil before stall, it shows that the corner vortices increase with the angle of attack, as well as the effect of sidewalls on the airfoil flow. After stall, the corner vortices decrease due to production of the three-dimensional separation cell. As for blunt airfoils, the results show that the enlarge of trailing edge weakens the influence of sidewalls on airfoil flow. The simulation results show that long vortex lines appear at both ends of the airfoil model due to corner vortices. Therefore, the effective angle of attack and the lift coefficient decrease but the drag coefficient increase due to the downwash of tip vortices. When the flow separates at large angles of attack, the sidewalls tend to suppress the separation under the specific model setup in this study.
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