标题： 飞机尾气中的非平衡相变：早期航迹形成计算研究 显示英文标题

标题： Non-Equilibrium Phase Changes in Aircraft Exhaust: A Computational Study on Early Contrail Formation

摘要： 建立了一种数值框架来模拟飞机发动机近场排气中的航迹形成，解析可压缩、多组分、非理想流体流动中的非平衡相变。 该方法结合了蒸汽涡轮机建模中用于液相转变的成熟方法和云微物理模型以模拟冰的形成。 它解析了均质和异质成核、相间动量交换以及液滴、冰晶和烟尘粒子的多分散尺寸分布。 这些模型在一个并行化的有限体积求解器中实现，并应用于具有简化几何形状的高旁通比涡扇发动机排气配置。 结果显示，非平衡效应强烈影响凝结和冻结动力学，而喷嘴几何形状和水蒸气含量调节局部过饱和度和相变路径。 研究结果强调了基于平衡的模型的局限性，并突显了基于物理、可扩展的工具在分析燃料和推进系统变化下的航迹形成中的价值。 显示英文摘要

摘要： A numerical framework is developed to model contrail formation in the near-field exhaust of aircraft engines, resolving non-equilibrium phase transitions in compressible, multi-component, non-ideal fluid flows. The approach combines well-established methods from steam turbine modeling for liquid-phase transitions with cloud microphysics models for ice formation. It resolves homogeneous and heterogeneous nucleation, interphase momentum exchange, and polydispersed size distributions of droplets, ice crystals, and soot particles. These models are implemented in a parallelized finite-volume solver and applied to a high-bypass turbofan exhaust configuration with simplified geometry. Results indicate that non-equilibrium effects strongly influence condensation and freezing dynamics, while nozzle geometry and water vapor content modulate local supersaturation and phase transition pathways. The findings underscore the limitations of equilibrium-based models and highlight the value of physics-based, scalable tools for analyzing contrail formation across fuels and propulsion systems.