尽管该风洞的尺寸很小，我们仍对翼型表面压力分布试验段的研制工作进行了大胆的尝试。
Although it is very small in size, some developments in the test section of pressure distribution on airfoil surface have been attempted.
通过数值求解定常跨音速流的无粘、小扰动方程，根据实心翼型或多孔翼型的边界条件，获得了相应的压力分布。
By numerically solving the inviscid, small disturbance equation in steady transonic regime, with boundary conditions on solid or porous airfoils, the corresponding pressure distribution is obtained.
可用于表面压力分布以及描述翼型边界层流的。
Surface pressure distribution can be used to describe the airfoil boundary layer flow well.
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