摘要
本文采用联立求解粘性剪切层和有旋无粘区的方法计算了再入钝头体层流近尾流场。有旋无粘区采用有旋特征线法计算。粘性剪切层采用改进的流管法计算，这两个区域间的基本流线上的压力、温度、速度等由两个区域迭代匹配确定，粘性剪切层的下边界区分流线采用实验确定，回避了回流区复杂计算，计算结果与有关试验和文献一致。本文的目的是提供远尾流计算所需的颈部初始剖面。
The near wake flow fields are calculated by simultaneously solving the viscous shear layer and the inviscid rotational region. The inviscid rotational region is solved by the use of rotational characteristics. However the viscous shear layer is calculated using the improved stream tubes. The presure, tempreture and velocity etc on the basic streamline streamline between these two regions are matched by the iteration method. The dividing streamline for the lower boundary region of the free shear layer is determined using the experiment, in order to avoid the complex calculation of the inverse region. The calculation results are agreement with the relative experiment and the references. The objective of the paper is to provide the primary profile of the neck for calculating the far wake.
出处
《宇航学报》
EI
CSCD
北大核心
1995年第3期69-75,共7页
Journal of Astronautics
