Abstract: According to the propulsion/airframe integrated design of aircraft， the variation study of intake and exhaust boundary condition under the influences of the propulsion system is carried out， making use of the parallelized in-house code and the adjoint equation code PADJ3D. Chain derivation is adopted to avoid the direct variation of the conservative variables. Then intermediate variables are introduced to reduce the variation difficulties of intake and exhaust boundary conditions. The sensitivity analysis method for design variables under the influences of the intake and exhaust effect is proposed. The numerical simulation accuracy of the analysis method is verified by calculation of the TPS standard model and comparison with the finite difference method. The proposed method is able to provide an efficient and reliable way for sensitivity analysis of design variables under intake and exhaust effect. Simulations are carried out for the aerodynamic layout of the engine on the wing. The intake and exhaust influences under various conditions (low speed， high speed / fixed angle of attack， constant lift， with and without propulsion system)， as well as the influencing mechanism， are simulated， analyzed and discussed. This research can provide technical support for the integrated design of pneumatic profile / propulsion system.

Key words: Variation of boundary conditions；Aerodynamic/propulsion system；Sensitivity information；Intake and exhaust effect；Adjoint equation

摘要： 面向飞行器内外流一体化设计，基于自主研发的大规模并行化结构化网格RANS求解器以及离散伴随方程求解器，开展了考虑推进系统动力状态下进排气边界条件的变分研究，通过链式求导法则避免直接对守恒变量变分，进一步引入中间变量大幅度简化了进排气边界条件变分的难度，建立了考虑进排气效应的设计变量灵敏度高效分析方法，并通过TPS标准模型计算验证了进排气数值模拟精度，与有限差分对比验证了灵敏度计算精度，以翼上发动机气动布局进排气影响数值模拟为例，系统分析了低速、高速、定攻角、定升力状态，推进系统有无动力工况灵敏度的变化以及影响机理。

关键词: 边界条件变分；气动外形/推进系统；灵敏度信息；进排气效应；伴随方程