提出了一种新型航空线性声衬结构——烧结金属丝网声衬，并在流管实验台上采用直接提取法对传统穿孔板声衬、金属丝网穿孔板声衬及该声衬分别开展掠流实验。实验采用了一个合适的入射声压级以排除高声强效应干扰。实验结果表明：传统穿孔板声衬的低频掠流声阻随掠流速度增加而升高，高频掠流声抗随着掠流速度增加而下降；金属丝网穿孔板声衬也存在这一趋势，但变化幅度有所减弱；而烧结金属丝网声衬因其去掉了传统穿孔板结构，采用烧结金属丝网作为声衬面板，提高了黏性声阻，从而使其掠流声阻抗在测试范围内基本不随掠流速度变化，相较于其他两种声衬对掠流具有更好的线性，更加符合航发外涵后传降噪最优声阻抗的变化趋势。

The sintered wire mesh liner， as a new aeronautical linear liner， is proposed. A grazing flow experiment is conducted on a flow duct set up using the straightforward method， which adopts an appropriate incident sound pressure level to exclude the high sound intensity effect， and a conventional perforated liner， a wire mesh perforated liner， and a sintered wire mesh liner are tested. This experiment shows that， for the conventional perforated liner， the grazing flow acoustic resistance at low frequencies and the grazing flow acoustic reactance at high frequencies exhibit significant increase and decreases as the flow velocity increases， respectively. As for the wire mesh perforated liner， this trends suppressed to some extent but still exists. However， the sintered wire mesh liner， which departs from the traditional perforated plate structure and uses sintered wire mesh as its liner panel， enhances its viscous acoustic resistance. As a result， both the resistance and reactance due to the grazing flow effect change very little within the tested flow velocity range. This liner offers superior linearity in response to grazing flow and is more consistent with the trend of the optimal acoustic impedance for aeroengine bypass backward noises.