小扰动方程，飞行学用语，是为了便于研究飞行器的稳定性和操纵性，在小扰动的前提下建立的方程。
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.
形象地表现线性小扰动运动方程的纵向和横航向典型运动模态，一直缺乏一种理想的方式。
There is no ideal way so far to represent the longitudinal and lateral motion mode of the small linear disturbance motion equation.
通过三个矢量方程组，系统地归纳了小扰动理论应用于多排叶片时各待定系数的关联方程。
By means of a three vector equation system, the correlative equations of the undetermined parameters are thus deduced when the small disturbance theory is applied to multiple blade rows.
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