摘要
针对一种双下侧布局带泄流腔的二元进气道进行了试验研究.试验时,来流速度范围Ma=2.0~3.5,姿态角范围为α=-4°~10°,β=0°~4°.试验获得了进气道的反压特性曲线、速度特性曲线、迎角特性曲线和侧滑角特性曲线.分析表明,随着来流速度和迎角的增加,进气道的流量系数先增加,在设计点达到最大,之后由于弹身头部激波的影响略有减小.侧滑时两侧进气道气流状态不同,工作范围由性能较低的迎风侧进气道来决定.另外,通过分析进气道的沿程静压分布曲线,说明泄流腔结构能使结尾激波停留在泄流腔边缘,扩大了进气道的工作范围.
A two-dimensional mixed-compression inlet model with slot-coupled cavity in 90° configuration at venter was investigated by wind tunnel at Mach number from 2.0 to 3.5.The range of the investigation covers angle of attack from-4° to 10° and angle of yaw from 0 to 4°.The performances,including critical pressure,total pressure recovery coefficient and mass flow ratio,were acquired.The results indicate that：with increase of the free stream Mach number or the angle of attack at Ma=3.0,the mass flow ratio increases firstly and then declines a little due to the increase of the total pressure loss around the body nose;and the maximum is obtained at design point.The flow field of two inlets is different at yaw,and the work range is determined by the windward inlet.Besides,the distribution of static-pressure coefficient along the duct validates that a terminal shock can stay around the cavity,so inlets with the slot-coupled cavity can work under wider back pressure.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第8期1818-1824,共7页
Journal of Aerospace Power
关键词
冲压发动机
超声速进气道
泄流腔
风洞试验
混压式
ramjet engine
supersonic inlet
slot-coupled cavity
wind tunnel test
mixed-compression
