摘要
气动热是制约高超声速飞行器设计的主要因素之一,当飞行高度大于40 km时流场中存在局部过渡区流动特性,基于分子动力学的DSMC方法是解决高超声速过渡区气动热计算的有效途径之一。针对高超声速飞行器的典型球锥外形,采用DSMC方法开展了过渡区流动气动热特性研究,分析了当流场具有过渡区流动特性时,飞行马赫数和飞行高度对气动热的影响规律,并与Fay-Riddell驻点热流的工程算法作了对比分析。计算结果表明,DSMC方法在高超声速过渡区流动气动热计算中可以得到较好的结果,适用于高超声速过渡区流场气动热的计算与分析。
Aerodynamic heating is one of important factors affecting hypersonic aircraft design. When the flight altitude is higher than 40 km, the transition regime flow takes on flow features of certain transitional region. The DSMC based＇on the molecular dynamics is one of the effective methods to calculate aerodynamic heating at hypersonic transition regime flow. In terms of one sphere-cone configuration, the present work studies the aerodynamic heating of the transition regime flow by DSMC method and analyzes the influence of flight Mach number and flight altitude on the aerodynamic heating. Then the data a- chieved are compared with the result of the Fay-Riddell method. The conclusion is that, DSMC method can perform very good result in calculating aerodynamic heating of hypersonic transition regime flow, and can be applied to the calculation and analysis of this issue.
出处
《现代防御技术》
北大核心
2010年第6期42-48,共7页
Modern Defence Technology
关键词
高超声速
过渡区
气动热
直接模拟蒙特卡罗
hypersonic
transition regime
aeroheating
direct simulation Monte Carlo（DSMC）
