论文部分内容阅读
采用DSMC/EPSM混合算法,研究了带有侧向喷流的复杂外形高超声速飞行器稀薄区和连续区三维混合流场的干扰特性。采用一种飞行器物面网格与DSMC计算域网格分别标识的方法,通过判断模拟分子与表面碰撞来完成飞行器物面网格与DSMC计算域网格间的信息传递和信息存贮,对于复杂外形飞行器的精确描述的物面网格不需做进一步处理,直接应用于不依赖于飞行器外形的DSMC计算的通用子程序中。引入碰撞数做为混合参数,对流动区域进行划分,并通过网格中碰撞数的统计和处理,有效地将DSMC和EPSM方法结合在一起。仿真计算了三维复杂外形飞行器带喷流流场压力、热流分布量,飞行器表面气动力、气动力矩和气动热参数,对喷流与高超声速空气绕流相互作用以及它们与物面之间的相互扰动进行了分析,证明了采用的方案和技术的有效性。
The DSMC / EPSM hybrid algorithm is used to study the interference characteristics of three-dimensional mixed flow field in the thin and continuous region of a complex hypersonic vehicle with a lateral jet. Using a method of object plane grid of aircraft and DSMC grid respectively, the information transfer and information storage between the plane plane of aircraft and the grid of DSMC are completed by judging the collisions between the simulated molecules and the surface. The accurately described object plane meshes of the profiled aircraft need not be further processed and applied directly to the generic subroutine of the DSMC calculation independent of the shape of the aircraft. By introducing the number of collisions as a hybrid parameter, the flow area is divided and the DSMC and EPSM methods are effectively combined through the statistics and processing of collisions in the grid. The pressure field, the distribution of heat flux, the surface aerodynamic force, the aerodynamic moment and the aerodynamic thermal parameters of a three-dimensional complex aircraft with a complex shape were simulated. The interaction between the jet flow and the hypersonic air flow and their interaction with the object surface Disturbances were analyzed and the effectiveness of the schemes and techniques employed was demonstrated.