《表1 来流参数：雷诺数对机翼尾缘噪声的影响（英文）》

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《雷诺数对机翼尾缘噪声的影响（英文）》

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Flow past a symmetric airfoil NACA0015with a sharp trailing edge is simulated.The freestream Mach number is M=0.2，and the Reynolds number based on the chord lengthCis chosen to be Rec=1×104 for low Reynolds number cases and Rec=5×104for moderate Reynolds number cases.Three angles of attack，0°，2°and 4°，are investigated.Details of the flow conditions are listed in Table 1.For simplicity，the simulation cases are labeled using the Reynolds number and the angle of attack.For instance，R1A0 represents the case operating at Reynolds number of Rec=1×104 and zero angle of attack.