摘要
高超声速气动加热问题一直是高超声速飞行器设计中的关键,是气动布局设计、结构设计以及热防护选材等的重要依据。然而气动热的数值模拟受到网格尺度、数值格式等多种因素的影响,是目前计算流体力学的难点之一。本文选择典型的三维钝锥模型,主要围绕网格尺度、数值格式精度以及耗散对高超声速气动热问题展开相关研究。结果表明,随着网格雷诺数的不断增加,热流计算值呈现不断减小的趋势,在气动加热比较严重的部位,热流计算值对于网格尺度的敏感性更强;网格尺度较小时精度越高,热流计算越准确,而网格尺度较大时,具有高分辨特性的MDADF-HY格式更为占优;同时,适当的耗散也是数值格式能够准确计算热流的前提。
Hypersonic aerodynamic heat has always been the key in the design of hypersonic vehicles,and it is also an important basis for aerodynamic layout design,structural design and material selection for thermal protection.However,the numerical simulation of aerodynamic heating is influenced by many factors,such as grid scale and numerical scheme,which is one of the difficulties in computational fluid dynamics.In this paper,a typical three-dimensional blunt cone model is selected,and the related research on hypersonic aerothermal problems is mainly focused on the grid scale,numerical scheme accuracy and dissipation.The results show that with the increasing of grid Reynolds number,the calculated value of heat flux shows a decreasing trend,and the calculated value of heat flux is more sensitive to the grid scale in the parts where aerodynamic heating is severe.When the grid scale is small,the higher the accuracy,the more accurate the heat flow calculation is.When the grid scale is large,the MDADF-HY scheme with high resolution is more dominant.At the same time,proper dissipation is also the premise that the numerical scheme can accurately calculate the heat flux.
作者
孙振生
王江彬
胡宇
毛凯
Sun Zhensheng;Wang Jiangbin;Hu Yu;Mao Kai(Rocket Force University of Engineering,Xi’an 710025,China)
出处
《航空兵器》
CSCD
北大核心
2022年第4期64-69,共6页
Aero Weaponry
基金
航空科学基金项目(201801U8001)
军科委基础加强领域基金项目(2019-JCJQ-JJ-103)。
