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提供了内部声激励增升机理的试验及数值研究结果，风洞试验就二元后台阶模型、平板、ＮＡＣＡ００１２翼型分别在两座不同的低速风洞中完成，试验和数值研究表明内部声激励能有效控制模型表面气流分离，有明显的增升效果，并从试验和数值计算两方面对声激励增升机理进行了较深入的探讨。
The experimental and numerical results of internal acoustic excitation enhancement mechanism are provided. The wind tunnel test is carried out on two back-stepped models with flat plates and NACA0012 airfoils in two different low-velocity wind tunnels respectively. The experimental and numerical studies show that the internal acoustic excitation Which can effectively control the air flow separation on the surface of the model, and has obvious effect of increasing the air pressure. The enhancement mechanism of acoustic excitation is discussed in depth from both the experimental and numerical calculation.