现代防御技术2017，Vol.45Issue(2)：74-79,92,7.DOI:10.3969/j.issn.1009-086x.2017.02.011
宽马赫数变几何进气道性能快速计算方法
Mathematical Model for Fast Design of the Variable Geometry Supersonic Inlets with Large Mach Number Range
徐珊珊 1金玉华 1张庆兵 2邵明玉3
作者信息
- 1. 中国航天科工集团第二研究院,北京100854
- 2. 北京电子工程总体研究所,北京100854
- 3. 西北工业大学航天学院,陕西西安710072
- 折叠
摘要
Abstract
A mathematical model for fast design of the two-dimensional variable geometry supersonic inlet with large Mach number range adaptive to preliminary design phase is established.The flow coefficient captured by inlet and critical total pressure recovery coefficient of inlet are obtained rapidly instead of solving directly for the flow conditions at each point in the flow.The geometrical position of the shock and inlet is employed to judge the inlet unstart phenomenon;the pseudo ideal throat hypothesis is built to calculate the first internal expansion;a set of shock-expansion is chosen to characterize the waves in throat.The present method is validated with high precision by comparing to inviscid CFD results.For the calculation of flow coefficient,the relative error is less than 5％ in most cases and increases along with the decrement of flow speed and increments of incidence angle and inlet ramp angle.For the calculation of critical total recovery coefficient,the maximal relative errors of geometry-variable inlet are around 4％,which increased with the increments of flow speed,incidence angle and inlet ramp angle.关键词
变几何进气道/超声速进气道/宽马赫数范围/快速建模方法/捕获流量系数/总压恢复系数Key words
variable geometry inlet/supersonic inlet/large Mach number range/mathematical model/flow coefficient captured by inlet/total recovery coefficient分类
军事科技引用本文复制引用
徐珊珊,金玉华,张庆兵,邵明玉..宽马赫数变几何进气道性能快速计算方法[J].现代防御技术,2017,45(2):74-79,92,7.
