摘要
以某二元混压式超声速进气道的流场数值计算结果为基础,得到超声速进气道主要内特性能参数与其进出口边界条件和几何结构参数之间的解析关系,此解析关系即为进气道的数学模型。根据此数学模型,研究了进气道与发动机之间的共同工作规律,并通过数值仿真分析了进气道二级斜板角度对进气道与发动机共同工作点的影响。
A mathematical model of supersonic inlet was studied by virtue of the numerical calculation results of the inner flow field for the 2D mix-compression supersonic inlet. The mathematical model described the relationship among the major performance parameters, in-and-out boundary conditions and the geometric configuration parameters. According to the mathematical model, the matching regulation between the inlet and aero-engine was studied. The influence of the second ramp angle upon the matching point of the inlet and the aero-engine was analyzed by means of the numerical simulations.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2003年第4期323-325,共3页
Journal of Propulsion Technology
关键词
超声速进气道
数学模型
航空发动机
进气道
发动机匹配
Compressibility of gases
Computer simulation
Geometry
Intake systems
Mathematical models
Supersonic flow
