热科学学报（英文版）2001，Vol.10Issue(2)：103-108,6.
Numerical Simulation of Integrative Flow Field for Hypersonic Vehicle
Numerical Simulation of Integrative Flow Field for Hypersonic Vehicle
HE Yuanyuan 1LE Jialing 1NI Hongli1
作者信息
- 1. Computational Aerodynamic Institute, China Aerodynamic Research and Development Center, Mianyang Sichuan 621000, China
- 折叠
摘要
Abstract
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.关键词
hypersonic vehicle/integration/finite volume methodKey words
hypersonic vehicle/integration/finite volume method分类
能源科技引用本文复制引用
HE Yuanyuan,LE Jialing,NI Hongli..Numerical Simulation of Integrative Flow Field for Hypersonic Vehicle [J].热科学学报（英文版）,2001,10(2):103-108,6.
