分布式电推进系统气动-推进耦合特性  

Aerodynamic-propulsion coupling characteristics of distributed electric propulsion system

作　　者：徐德 许晓平[1] 夏济宇 周洲[1] XU De;XU Xiaoping;XIA Jiyu;ZHOU Zhou(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空动力学报》2024年第9期181-196,共16页Journal of Aerospace Power

基　　金：陕西省重点研发计划(2021ZDLGY09-08)。

摘　　要：采用了基于k-ωSST(shear stress transpot)湍流模型求解雷诺平均Navier-Stokes(RANS)方程的动量源方法(MSM),针对带增升襟翼的分布式动力机翼二维简化模型,开展了垂直起飞-过渡-巡航飞行状态下的气动-推进耦合特性及物理机理研究。研究表明:涵道的抽吸效应使分布式动力机翼呈现增升减阻现象,并推迟了机翼流动分离。相比于自由来流条件,涵道喷流中的增升襟翼失速偏角从12°显著增大到34°,同时增升襟翼诱导喷流偏转,使分布式动力构型总升力得到有效提升。A momentum source method(MSM)for solving the Reynolds average Navier-Stokes(RANS)equations based on the SST(shear stress transpot)turbulence model was adopted.For the two-dimensional simplified model of the distributed propulsion wing with lift flaps,research on the aerodynamic-propulsion coupling characteristics and physical mechanism in the vertical take-off,transition and cruise flight state was carried out.The research showed that the suction effect of the duct made the distributed propulsion wing show the phenomenon of increasing lift and reducing drag,and delayed the flow separation of the wing.Compared with the freestream condition,the stall declination angle of the lift flaps in the ducted jet significantly increased from 12°to 34°,and at the same time the lift flaps induced jet deflection,so that the total lift of the distributed propulsion configuration was effectively raised.

关 键 词：分布式电推进 垂直起降(VTOL) 增升襟翼 动量源方法 抽吸效应 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]