摘要
通过求解三维可压缩N S方程组,对尖锥/圆柱组合体模型在超音速绕流中的侧向喷流干扰流场进行了模拟,数值方法采用有限体积法,差分格式采用NND格式。分析了干扰流场的结构,研究了干扰效应对气动性能的影响,得到来流Ma∞=3 3和4 5时力放大因子和干扰力矩系数随攻角变化的规律,计算结果与实验一致。
The flow field of lateral jet interaction with an external supersonic flow is simulated for ogive/cylinder configuration by solving the 3-D, compressible N-S equations. The finite volume method based on the NND scheme is adopted to deal with the governing equations. The field structure is obtained and the interaction effects on aerodynamic character are studied. The regulations about effects of angles-of-attack on the factor of amplification and the moment coefficient of interaction at Ma∞=3.3 and 4.5 are performed. The CFD results agree well with the experiment.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2004年第2期108-112,共5页
Acta Aeronautica et Astronautica Sinica
关键词
侧向喷流
干扰
超音速
数值模拟
Aircraft
Computer simulation
Finite volume method
Flow interactions
Fluid dynamics
Jets
