摘要
乘波体在高空高超声速飞行时,流场温度急剧升高,气体热力学性质发生改变,其气动特性与采用完全气体模型得到的结果存在差异,因此在飞行器设计中开展真实气体效应影响研究具有重要的工程价值。本文针对锥导乘波体设计提出了一种考虑平衡气体效应的特征线方法(Method of characteristic, MOC),基于不同半锥角和不同流动捕获曲线生成了不同外形的乘波体,并使用快速估算方法估算平衡气体条件和完全气体条件下各乘波体的气动特性和几何特征参数,研究了不同气体模型对乘波体设计结果的影响。研究结果表明,高马赫数下基于平衡气体模型设计得到的乘波体升阻比、容积率和俯仰力矩系数等特性参数相比完全气体结果存在差异,并且平衡气体效应对不同外形乘波体的影响程度和影响规律不同。
As the flow temperature rises dramatically at high altitudes and hypersonic speeds,the thermodynamic properties of gas change,causing changes in aerodynamic properties of waverider.Therefore,it is of great engineering value to investigate real gas effects in the design of waverider.A method of characteristic(MOC)considering equilibrium gas effect is proposed for the design of cone-derived waverider.Different shapes of waverider are generated based on different half cone angles and different flow capture curves,and the aerodynamic and geometrical characteristics of each waverider under equilibrium gas and perfect gas conditions are estimated using a fast estimation method.The results shows that there are differences in the lift-to-drag ratio,volume ratio and pitch moment coefficient of the waverider designed based on the equilibrium gas model at high Mach number compared with the perfect gas results.The degree and pattern of the influence of equilibrium gas effect on different configurations of waverider are distinct.
作者
林鹭颖
李沁
严攀
翁谊辉
尤延铖
李留刚
LIN Luying;LI Qin;YAN Pan;WENG Yihui;YOU Yancheng;LI Liugang(School of Aerospace Engineering,Xiamen University,Xiamen 361102,China;Science and Technology on Space Physics Laboratory,China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2024年第1期163-175,共13页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
高超声速
平衡气体
乘波体
特征线方法
气动特性
hypersonic
equilibrium gas
waverider
method of characteristic(MOC)
aerodynamic characteristics
