双S形进气道流场数值计算与分析  

Number simulation and analysis of double s-shaped inlet

作　　者：朱彦伟[1] 高扬[1] 刘旭东[1] 

机构地区：[1]中国飞行试验研究院发动机所,西安710089

出　　处：《机械设计与制造》2010年第4期234-236,共3页Machinery Design & Manufacture

基　　金：国家973计划资助项目(2007CB707701)

摘　　要：为了考察飞行攻角对进气道性能的影响,采用k-ε湍流模型对某型飞机的双S形进气道内外流场进行了综合求解,分析了飞行攻角对进气道总压恢复系数和出口总压畸变的影响。结果表明:进气道出口的总压分布是由进口的气流条件决定的,攻角小于(-5)°和大于23°时,总压恢复系数随飞行攻角的变化明显,攻角在(-5～23)°之间变化时总压恢复系数变化量不大,当攻角为10°时总压恢复系数达到最大值0.9844;当飞机在小于(-10)°或大于30°攻角飞行时,进气道出口总压畸变程度较大。In order to study the influences of flight attack angles on inlet characteristic,k-ε turbulence models was used to predicting the flow field of double S-shaped inlet. According to the calculated results,we have analyzed the influences of flight attack angles on total pressure recovery coefficient and total pressure distortion. It shows that when flight attack angles less than （-5）° or exceed （23）° ,recovery coefficients sensitive to flight attack angles;When flight attack angles in range of （-5-23）°,the variety of recovery coefficient is small; Recovery coefficient up to top on attack angles at 10°. When flight attack angles less than （-10）° or exceed （30）°,exit total pressure distortion of inlet is serious ;Exit total pressure distortion is decided by entry flow conditions.

关 键 词：双S形进气道 总压恢复 总压畸变 

分 类 号：TH12[机械工程—机械设计及理论] E926.3[军事—军事装备学]