摘要
采用计算流体力学方法,针对飞翼布局无人机涡扇发动机喷流问题开展了数值模拟研究。首先,应用Reynolds平均Navier-Stokes方程数值模拟方法,对典型飞翼布局无人机数值模拟进行了网格无关性验证;其次,探讨了在工程设计中,由于喷流导致无人机产生的外形变化带来的气动特性差异;最后,针对典型工况下不同落压比喷流条件,研究分析了涡扇发动机喷流效应对无人机气动特性的影响规律。研究结果表明:喷流导致飞翼布局无人机外形发生变化,因此带来6%~9%阻力系数的增量,并使俯仰力矩系数下移;而喷流效应主要影响无人机阻力系数和俯仰力矩系数,影响规律随落压比而变化。
The turbofan engine exhaust simulation is carries out for the flying wing UAV by the means of computational fluid dynamics.Firstly,the grid convergence study is performed with course,medium,and fine grid systems for the flying wing UAV through Reynolds-averaged Navier-Stokes equations and structured grid technology.Secondly,the change of the aerodynamic performance caused by the difference between the flying wing configuration with engine exhaust and without engine exhaust is discussed in the engineering design.Lastly,the turbofan engine exhaust effect is studied with three different nozzle pressure ratio conditions.The study shows that,the change of the configuration generated by engine exhaust makes the drag increased 6%-9%and pitching moment decreases.The engine exhaust has an effect on drag coefficient and pitching moment coefficient,and the influence quantities are varied with the nozzle pressure ratio.
作者
张翔
曹德一
何海波
崔飞
ZHANG Xiang;CAO Deyi;HE Haibo;CUI Fei(Beijing Institute of Mechanical and electrical engineering,Beijing 100074,China)
出处
《空气动力学学报》
CSCD
北大核心
2019年第4期578-585,共8页
Acta Aerodynamica Sinica
关键词
计算流体力学
飞翼布局
喷流
气动特性
涡扇发动机
落压比
computational fluid dynamics
flying wing
engine exhaust
aerodynamic performance
turbofan
nozzle pressure ratio
