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本文通过解跨声速小扰动方程求解假想外场，给出进行自适应壁风洞实验的迭代方案。用此方案，在堵塞比ε＝８％，实验段高弦比Ｈ／Ｃ＝１．５的情况下，对ＮＡＣＡ００１２翼型进行了高亚声速、迎角６°以下的验征性实验，实验结果与国外大风洞无干扰数据符合较好。同时，本文还给出了另一种自适应壁风洞实验方案：一步法，并将用此方法算出的壁面形状与迭代法的收敛壁面形状作了比较。结果表明：二者具有较好的一致性。本文研究表明：两种方案均有很好的应用前景。
In this paper, we solve the hypothetical field by solving the transonic small perturbation equation, and give an iterative scheme for adaptive wall-wind tunnel experiments. With this scheme, the NACA0012 airfoil was tested for high subsonic velocity and angle of attack below 6 ° with the plugging ratio ε = 8% and the high-to-high ratio of experimental section H / C = 1.5. Results with foreign wind tunnel no interference data in good agreement. At the same time, this paper also gives another experimental scheme of adaptive wall wind tunnel: one-step method, and compares the wall shape calculated by this method with the convergent wall shape of iterative method. The result shows that the two have good consistency. This study shows that: Both schemes have good application prospects.