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进气道尾喷管的存在不仅影响着飞机机身前后的流场特性与压力分布,而且影响着飞机升力特性、阻力特性以及力矩特性.为了研究进排气效应对飞机气动特性的影响,采用计算流体力学(CFD)数值模拟技术,建立飞翼布局无人机(UAV)堵锥整流模型和动力影响模型,其中动力影响模型是根据发动机不同的工作状态,在进气道以及尾喷管截面上设置不同的边界条件,对比分析这两种计算模型在流场特征和气动特性上的差异性,揭示内在的影响机理.进排气效应的研究有助于飞机/发动机的一体化气动综合设计.
The existence of inlet nozzle not only affects the flow field characteristics and pressure distribution around the aircraft fuselage, but also affects the aircraft lift characteristics, drag characteristics and torque characteristics.In order to study the intake and exhaust effects on the aerodynamic characteristics of the aircraft, Computational Fluid Dynamics (CFD) numerical simulation technology, the establishment of flying wing layout UAV plug cone rectifier model and dynamic impact model, in which the dynamic impact model is based on different engine operating conditions, in the intake port and the nozzle section Set different boundary conditions, comparative analysis of these two models in the flow field characteristics and aerodynamic characteristics of the differences and reveal the inherent mechanism of the impact of intake and exhaust air-to-aircraft research contribute to the integrated aerodynamic design .