冲压发动机进气道和掺混段节流特性数值研究  

Numerical study of the throttle characteristicabout the ramjet inlet and mixing section

作　　者：白鹏[1] 朱守梅[2] 孟宇鹏[2] 李稳绪[2] 马汉东[1] 周伟江[1] 

机构地区：[1]北京空气动力研究所,北京100074 [2]航天科工集团公司31所,北京100074

出　　处：《推进技术》2004年第6期503-507,共5页Journal of Propulsion Technology

摘　　要：为了研究冲压发动机进气道和掺混段节流特性及其内部的复杂流动,以同试验进行对比,采用二阶迎风隐式TVD格式,内外流分区求解可压缩N S方程,数值模拟弹体,进气道和掺混段一体化通气模型复杂流场。进气道为"X"型布局二元双楔平面压缩混压式进气道,掺混段为圆形截面。计算了掺混段出口反压比pt pt∞=3 5～5 5,总压恢复系数σ,流量系数φ及流场情况。同风洞试验结果比较表明:计算结果较为合理。通过对计算结果的分析,定性讨论了该冲压发动机的节流特性和掺混段内部复杂流动状况。To investigate the characters of the throttle about the ramjet inlet and mixing section, while to compare with the experimental results, the second order upwind implicit TVD schemes were used to solve the compressible N-S equations for integrated simulating the complex inner and outer flow fields about the missile body, ramjet inlet and mixing section. The 2-D inlets with two compression plane were configured in X type. The mixing section is circle. The total pressure recovery coefficient σ, the coefficient of the flux φ and the flow fields were presented, where the pressure ratio between mixing section exit and free stream pt/pt∞ = 3.5-5.5. The present results were compared with the experimental results. The complex flow fields were discussed.

关 键 词：冲压喷气发动机 进气道 掺混段 节流特性 内外流场 一体化数值模拟 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]