高超声速激波/边界层干扰流动数值模拟研究  

Numerical study on hypersonic double-cone separated flow

作　　者：龚安龙[1] 刘周[1] 杨云军[1] 周伟江[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2014年第6期767-771,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(11372040)

摘　　要：在基于Roe格式的全Navier-Stokes方程计算流体力学(CFD)代码中,发展了一种局部熵修正方法,克服了传统熵修正方法在边界层流动模拟中耗散过大的缺点,可用于更加准确的模拟激波/边界层干扰的复杂高超声速流动。对典型高超声速双锥边界层分离与激波干扰的复杂流动进行了模拟,研究了网格密度和熵修正方法耗散性对计算结果的影响。研究表明:高超声速双锥边界层分离与激波干扰流动的数值模拟结果对网格具有很强的敏感性,过稀的网格将产生严重的分离流动预测偏差;低耗散性的局部熵修正方法能更加准确地模拟复杂的高超声速激波与边界层分离流动干扰现象。A portion entropy fix method was developed in a computational fluid dynamic（CFD）code based on Navier-Stokes techniques with Roe′s scheme.The portion entropy fix method overcomes the short-age of large dissipation in boundary layer simulations that traditional entropy fix method generally may pos-sess and achieves more accurate simulation results of complex hypersonic viscous flows with shock wave/boundary layer interaction.In this paper,the typical hypersonic double-cone separated flows with shock wave interactions are computed by the code.The grid sensitivity and the entropy fix method dissipation effects are studied.From the analysis,the simulation results of hypersonic separated flows with shock wave interactions are very sensitive with grid refinement,and coarse grid will give large departure;portion entropy fix methods with low dissipation obtaines more credible solution for complex hypersonic separated flows with strong shock wave interactions.

关 键 词：计算流体力学 高超声速 激波/边界层干扰 熵修正 网格敏感性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]