Numerical Simulation of Integrative Flow Field for Hypersonic Vehicle

作     者：HE Yuanyuan LE Jialing NI Hongli Computational Aerodynamic Institute, China Aerodynamic Research and Development Center, Mianyang Sichuan 621000, China 

作者机构：Computational Aerodynamic Institute China Aerodynamic Research and Development Center Mianyang China 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2001年第10卷第2期

页      面：103-108页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0805[工学-材料科学与工程（可授工学、理学学位）] 0702[理学-物理学] 0801[工学-力学（可授工学、理学学位）] 

主　　题：hypersonic vehicle integration finite volume method. 

摘      要：To meet the requirements for the aerodynamic performance and thrust force demanded in hypersonic missions, the integration design of fuselage and. engine must be considered for hypersonic vehicle with a scramjet engine. The configuration of wave rider is a typical hypersonic vehicle shape, whose fore-body can compress the flow in advance and provide uniform flow for the air intake, and whose aft-body,is used as an expansion surface of nozzle. In the present paper, an engineering method is applied to define total aerodynamic characteristics of an approximate wave rider configuration. A finite volume method based on the center of grid is also employed to numerically investigate the outflow pass the same configuration. The flow field details and the aerodynamic characteristics at given conditions are obtained. The evaluation for this configuration may be used as a guide for the hypersonic vehicle experiment.