摘要
首先,将无网格方法用于带化学反应的多组分气体Euler方程进行求解,给出无网格条件下求解化学非平衡流的具体过程;其次,对NACA0012跨声速绕流场、楔体斜爆轰流场进行了数值模拟,验证无网格算法的可靠性以及无网格算法能否用于复杂化学非平衡流数值模拟中;最后,采用发展的无网格算法计算了典型火箭燃气射流流场。计算结果表明,采用无网格算法能较好地模拟复杂化学非平衡流场,正确分辨复杂的物理现象;在欠膨胀状态下,相交射流激波在轴线上的交点随着欠膨胀程度的增加而远离喷管出口。在过膨胀状态下,相交射流激波在轴线上的交点随着过膨胀程度的增加而不断靠近喷管出口;超声速来流条件下,仅改变不同来流马赫数,对射流流场总体结构基本无影响,射流激波相交点位置基本相同,轴线上参数分布也基本一致。为研究火箭燃气射流流场提供了一种新的数值方法,并拓宽了无网格算法的应用范围。
The gridless algorithm was applied to solve the multicomponent gas Euler equations with chemical reactions at first, and the solving process was given at gridless conditions.Then,in order to verify the gridless algorithm＇s ability of numerical simula tion of complex chemical nonequilibrium flow, NACA0012 in transonic flow field and wedge oblique detonation flow field were com puted.Finally, typical rocket gas flow field was simulated by using gridless algorithm.The results of numerical simulation show that the use of gridless algorithm can simulate the complex chemical nonequilibrium flow field and correctly distinguish the complex physical phenomena;at underexpanded state, the intersection point of the intersecting jets shock is away from the nozzle exit with increasing of the underexpanded degree of jets;at overexpanded state, the intersection point of the intersecting jets shock is close to the nozzle exit with increasing of the overexpanded degree of jets; at supersonic flow conditions, the overall structure of the jet flow field is not affected by changing the stream Maeh number, the position of jet shock intersection point is basically the same, and the axial parameter distributions are also basically the same.This paper provides a new numerical algorithm for the research on the flow field of rocket gas, and broadens the applications range of gridless algorithm.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2014年第1期23-29,共7页
Journal of Solid Rocket Technology
