高气动性能、复杂构型的多维偏转S弯喷管气动型面设计是翼身融合布局隐身飞机的关键技术之一。通过改进Lee曲线方法和多参数耦合法，提出了一种异型喷口的多维偏转S弯喷管设计方法，实现了带矢量角的多维偏转S形中心线设计和圆形进口至异型喷口的截面过渡，可用于常规及空间受限布局下的多维偏转、带矢量角、非对称异型喷口、单/双发布局等多种类型的S弯喷管气动型面设计。基于数值模拟方法和小型涡喷发动机整机实验验证了提出的设计方法，结果表明：基于空间受限布局设计的超紧凑S弯喷管，在临界工况下，流量系数达到0.982，推力系数达到0.989，在超临界工况下，流量系数不小于0.984，推力系数不小于0.992；基于空间受限布局设计的多维偏转S弯喷管，在临界工况下，流量系数达到0.980，推力系数达到0.986，在超临界工况下，流量系数不小于0.981，推力系数不小于0.990；基于双发布局设计的双发S弯喷管，安装发动机后总推力相比原装喷管降低不大于4.58%，具有较好的气动性能。

The aerodynamic profile design of multi-dimensional deflected serpentine nozzles with high aerodynamic performance and complex configurations is one of the crucial technologies for stealth aircraft with integrated wing-body layouts. By improving the Lee curve method and multiparametric coupled method， we propose a design method for multi-dimensional deflected serpentine nozzles with an abnormal exit， and realize the multi-dimensional deflected serpentine centerline design with vector angles and the cross-sectional transition from the circular inlet to the abnormal exit. This method can be used for the aerodynamic profile design of multiple serpentine nozzles with conventional and space-confined layouts， such as multi-dimensional deflected serpentine nozzles， serpentine nozzles with vector angles， serpentine nozzles with unsymmetrical abnormal exits， and serpentine nozzles for single and twin aeroengine layouts. The proposed design method is verified by the numerical simulation method and the small turbojet engine test. The results show that the discharge and thrust coefficients of the ultra-compact serpentine nozzle designed with the space-confined layout reach 0.982 and 0.989， respectively， under the critical condition， and are no smaller than 0.984 and 0.992， respectively， under the overcritical condition. Those of the multi-dimensional deflected serpentine nozzle designed with the space-confined layout reach 0.980 and 0.986， respectively， under the critical condition and are no smaller than 0.981 and 0.990， respectively， under the overcritical condition. The total thrust of engine after installing the juxtaposition serpentine nozzles designed with the twin engine layout is no more than 4.58% lower than that with the original nozzle. The designed serpentine nozzles have better aerodynamic performance.