稀薄过渡流区横向喷流干扰效应数值模拟研究

摘要

A parallel DSMC method is presented for accuratly predicting the effects of lateral jet interaction with rarefied atmosphere of transition flow.A hybrid grid structure with Cartesian coordinate meshes and surface unstructured triangular cells is developed with collision cells adaptation and used in the DSMC computation.A static random load balancing technique is applied in the parallel DSMC code using the MPI parallel environment.For the computation of lateral jet interaction of three-dimensional plat plate model with different pressure ratios, the results of surface separation distance show good agreement with low density wind tunnel experiment to validate the DSMC algorithm.The supersonic and hypersonic RCS jet interaction with hypersonic rarefied incoming flow on a slender blunt double-cone in rarefied transition flow regime are investigated.The impacts of flight altitude, free stream velocity, angle of attack and jet thrust on plume-atmosphere interaction flow fields and aerodynamic properties are numerically analyzed.The influences of parameter distributions with uniform /non-uniform of nozzle exit on the seperation distance and votex structure near the jet are simulated in detail.%为了准确预测稀薄过渡流区横向喷流与稀薄大气的干扰流动特征,本文在建立直角与表面非结构网格混合结构的DSMC数值算法以及碰撞网格自适应算法基础上,提出基于MPI的静态随机负载平衡技术,构建了DSMC并行计算代码.计算的不同压力比条件下三维平板模型横向喷流与稀薄大气干扰的分离长度与低密度风洞试验有较好的一致性,验证了本文算法的可靠性.开展了细长钝双锥外形高超声速稀薄来流与超声速/高超声速横向喷流干扰效应的研究,计算分析了不同飞行高度、不同飞行速度、不同飞行攻角、不同喷流推力下复杂流场结构和对气动力特性的影响规律.考察了RCS喷管出口参数不同(均匀/非均匀)对喷口附近分离涡和分离长度的影响.