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整流罩设计对基于分布式动力的翼身融合飞机气动特性会产生显著影响。为了揭示在边界层吸入效应下整流罩的设计参数对飞机气动特性的影响及其原因，本文采用计算流体力学（CFD）方法和 Morris 敏感度分析法对此布局飞机气动特性进行了详细研究，得到了整流罩主要设计参数对飞机气动特性影响的敏感度和耦合关系，并对典型设计参数下的流动特性进行分析。结果表明：对飞机气动特性影响较大的参数是整流罩特征截面 2 和 3 的最大厚度，这是因为其增大了当地截面的厚度和弯度，进而影响了整流罩表面的压力分布；在流量系数减小和进气边界弦向位置前移时，最大厚度增大会造成背风面发生局部分离；整流罩特征截面 2 和 3 的最大厚度对气动特性的耦合影响作用相对较强。
The cowl design has a significant effect on the aerodynamic characteristics of a wing-based fusion aircraft based on distributed dynamics. In order to reveal the influence of the design parameters of the fairing on the aerodynamic characteristics of the aircraft under the effect of the suction in the boundary layer and its causes, this paper studies the aerodynamic characteristics of the aircraft with CFD and Morris sensitivity analysis in detail, and obtains The main design parameters of the fairing on the aerodynamic characteristics of the aircraft sensitivity and coupling, and the typical design parameters of the flow characteristics of the analysis. The results show that the parameters that affect the aerodynamic characteristics of the aircraft are the maximum thickness of the characteristic sections 2 and 3 of the fairing because they increase the thickness and curvature of the local section and thus affect the pressure distribution on the surface of the fairing. When the coefficient decreases and the chord direction of intake boundary moves forward, the maximum thickness increases and causes the partial separation of leeward surface. The maximum thickness of characteristic sections 2 and 3 of fairing has a relatively strong influence on the coupling of aerodynamic characteristics.