摘要
采用块结构网格与二阶精度流场分区求解技术,对高速旋转、含侧向支柱冲压增程弹丸进气道内外复杂流场进行了数值模拟,得到了高速旋转工况下对应于不同来流马赫数和攻角,以及临界工况时超音速进气道内外流场复杂的波系结构。在旋转工况下,进气道流场结构与不旋转时相似,但旋转速度以及攻角的存在对冲压发动机进气道的总体性能产生了负面影响,进气道总压恢复系数和动能系数均有所降低,而流场畸变指数则显著增大;冲压发动机进气道在较低马赫数工作时的综合性能优于在较高马赫数工作时的综合性能。
Complex flow field in air inlet of high-speed spinning ramjet extended range projectiles was numerically simulated by using block structure grid and second-order precision zonal solving method. Under the high-speed spinning work condition, complex wave system structures of supersonic air inlet at different inflow Mach number and attack angle were obtained. Flow field structure in air inlet under spinning work condition is similar to that under non-spinning work condition. But spinning velocity and attack angle have negative influence on system performance of ramjet inlet. The total pressure recovery coefficient and the kinetic energy coefficient of air inlet decrease, while the flow distortion index increases obviously. Comprehensive properties of ramjet inlet under low mach number are superior to that under high mach number.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2006年第4期243-246,共4页
Journal of Solid Rocket Technology
