Numerical simulation of flow past a flat plate with anti-singing trailing edge

摘要

Aerofoil with anti-singing trailing edge has been seen as the treatment to eliminate singing. The present study numerically investigates the bevel and chamfer anti-singing nailing edges with rounded ones in flat plates. The effects of 25°, 45°, 10° bevel and 15°, 45° chamfer angles provided at the trailing edge of the flat plate on the aerodynamic characteristics are systematically compared with rounded ones at a Reynolds number of 1.5x 10~5 and 25°, 30° and 45° angle of attack. The substantial reduction of primary vortex shedding frequency is observed in 25°, 45°, 10° bevel and 15°, 45° chamfer trailing edges as compared to the rounded one. Also, the presence of broader wake profile indicates higher drag in rounded trailing edge geometry as compared to anti-singing trailing edges. Thus, the present study demonstrates that the 45° and 10° bevel trailing edge could provide better anti-singing behavior and aerodynamic performance in comparison with 25° bevel, 15°, 45° chamfer and rounded trailing edge.