摘要
为了对超声速进气道内激波/边界层干扰控制进行研究,将进气道简化为平板/楔形体结构,用数值方法研究一段包线上吹除法抑制气流分离的性能变化趋势以及吹除气体总压、喷嘴高度对吹除性能的影响。研究表明,吹除法在一定马赫数范围内能抑制气流分离,马赫数超过设计点后,随着马赫数增大吹除性能降低。达到吹除效果后增大吹除压力和增加喷嘴高度不能提高吹除性能。随着来流马赫数增大,气流抗反压能力增强,气流分离减少。
In order to study the shock wave/boundary layer interaction control, two - dimensional flat/ wedge structure was used to simplify supersonic inlet, and numerical simulation method was used to study the tendency of blowing effect under different flow Mach number. Furthermore, the effects of the blowing to- tal gas pressure, blowing nozzle height and other parameters on the inhibition of boundary layer airflow sepa- ration were discussed. Results show that the blowing method can effectively inhibit the flow separation under a range of flow Mach number, and when the flow condition deviates from the design point, the performance of the blowing method degrades as the increase of Mach number. Increasing the blowing pressure or the blo- wing nozzle height cannot improve the effect of blowing. With increasing the flow Mach number the flow anti pressure ability is enhanced, and flow separation is reduced.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第10期1310-1315,共6页
Journal of Propulsion Technology
基金
北京航空航天大学研究生科技创新实践基金(YCSJ-01-201207)
关键词
超声速进气道
激波
边界层干扰控制
吹除法
变马赫数
数值仿真
Supersonic inlet
Control of shock/boundary layer interaction
Blowing method
Differentflow Mach number
Numerical simulation
