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

作　　者：徐珊珊[1] 金玉华[1] 张庆兵[2] 邵明玉[3] XU Shan-shan JIN Yu-hua ZHANG Qing-bing SHAO Ming-yu(The Second Research Academy of CASIC, Beijing 100854, China Beijing Inst. of Electronic System Engineering, Beijing 100854, China Northwestern Polyteehnical University,College of Astronautics,Shaanxi Xi＇ an 710072, China)

机构地区：[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

出　　处：《现代防御技术》2017年第2期74-79,92,共7页Modern Defence Technology

摘　　要：提出一种适用于初步设计的宽马赫数变几何超声速进气道性能快速计算方法,无需计算流场各点参数即可快速获得捕获流量系数φ和临界总压恢复系数σ。利用激波与进气道的几何关系判断起动;采用虚拟喉道假设计算第一道内压膨胀波;采用一组激波-膨胀波模拟喉道内复杂波系。为检验方法正确性,计算结果与无粘CFD结果进行了比对。φ相对误差在5%以内,随马赫数减小、攻角或楔板折角增大而增大;σ最大相对误差为4%,随马赫数、攻角、楔板折角增大而增大。A mathematical model for fast design inlet with large Mach number range adaptive to preli of the two-dimensional variable geometry supersonic minary design phase is established. The flow coeffi- cient 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 resuhs. 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 

分 类 号：TJ760.33[兵器科学与技术—武器系统与运用工程] TJ760.11