基于隐式大涡模拟的高超声速热流计算研究  

Study on Hypersonic Heat Flow Calculation Based on Implicit Large Eddy Simulation

作　　者：王杨[1] 周丹杰[1] 王超[1] 

机构地区：[1]北京机电工程研究所,北京100074

出　　处：《航空科学技术》2015年第10期60-67,共8页Aeronautical Science & Technology

摘　　要：传统的大涡模拟方法面临着很多的困难,新提出的隐式大涡模拟可以作为解决这些挑战的一个方法。目前,隐式大涡模拟方法主要是在有限体积法中应用,也可将隐式大涡模拟应用于有限差分方法,使方程的截断误差更容易被控制,提高了隐式大涡模拟方法的精度。首先推导了有限差分方法中隐式大涡模拟的方程以及证明了其有效性,并提出了有限差分方法应用隐式大涡模拟方法数值计算的要求,隐式大涡模拟方法具有应用简单、普适性强、计算效率高的特点。最后编写了隐式大涡模拟方法的程序进行了数值试验,应用于高超声速湍流流场的热流计算,验证了方法的正确性。The traditional method of large eddy simulation met many dififculties, the Implicit Large Eddy Simulation（ILES） is a new method to these challenges, the current ILES is mainly used in the ifnite volume method, in this paper, ILES was applied using ifnite difference method, so that truncation error equation easier to control and improve the precision of ILES. Firstly, the ifnite difference method was derived in ILES equation and proved its effectiveness, the ILES method application is simple, universal, high computing efifciency. Finally, the ILES program was compiled, which was applied to numerical experiment for hypersonic turbulent lfow to verify the method.

关 键 词：隐式大涡模拟 高超声速 有限差分 湍流 

分 类 号：O355[理学—流体力学]