摘要
数值模拟高超声速飞行器定常飞行时,需要给定壁面合适的温度条件以得到足够精确的预测结果。针对高超声速飞行器在风洞吹风试验与高空真实飞行时的壁面温度特性显著不同,分析了两类不同条件下数值模拟中壁面温度条件的选取问题。采用数值模拟方法求解三维Navier-Stokes方程,研究了壁面温度在风洞试验状态和高空飞行状态下对类HTV-2高超声速飞行器气动性能和边界层内特性参数的影响规律,结果表明:风洞试验条件下和高空飞行状态的壁面温度影响气动力机理不同导致壁面温度条件选取准则不同。
For numerical simulation of hypersonic vehicle in steady flight,it is necessary to give appropriate wall temperature conditions to obtain accurate prediction results.Since the wall temperature characteristics of hypersonic vehicle in wind tunnel test and real flight at high altitude are significantly different,the selection of wall temperature conditions in numerical simulation under two different conditions needs to be studied in detail.Three-dimensional Navier-Stokes equations are solved by numerical simulation method,and the influence of wall temperature on aerodynamic performance and boundary layer characteristic parameters of HTV-2 hypersonic vehicle under wind tunnel test and high-altitude flight conditions is studied.The results show that the influence of wall temperature on aerodynamic is different between wind tunnel test condition and high-altitude flight condition,leading to different selection criteria of wall temperature conditions.
作者
陶善聪
周毅
时晓天
TAO Shancong;ZHOU Yi;SHI Xiaotian(China Academy of Aerospace Aerodynamics,Beijing 100074,China;School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2023年第10期250-257,共8页
Journal of Ordnance Equipment Engineering
基金
国家自然科学基金项目(11872348,11802297)
国家重点研发计划(2019YFA0405300).
关键词
高超声速
气动力预测
壁温
CFD
hypersonic
prediction of aerodynamic force and moment
wall temperature
CFD
