摘要
采用薄激波层理论和流管质量守恒相结合的方法,分析了高超声速二维钝楔边界层外缘熵的分布规律,研究了熵层对边界层外缘密度、马赫数以及壁面气动加热等气动参数的影响.结果表明:边界层外缘熵在倒圆-肩部区下降最为剧烈,熵层对气动参数的影响在高超声速下不可忽略,特别是使转捩区和湍流区的气动加热增加约53.6%.因此,将表面流态控制在层流模式对高超声速飞行器热防护具有重要意义.
Using thin shock layer theory and mass conservation of stream tube, the en- tropy distribution of boundary layer exterior margin was analyzed for hypersonic two-dimen- sional （2-D） blunt wedge, and the influence of entropy layer on aerodynamics parameters such as density, Mach number, and aeroheating, et al. , was investigated. The results show that the entropy of boundary layer exterior margin dropped more quickly in rounding- shoulder region, and the influence of entropy layer on aerodynamics parameters should not be neglectable, which especially augmented the aeroheating 53.6% in transition and turbu- lent region. So, controling the flow of wall to stay in laminar model is very important for thermal protection of hypersonic vehicle.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第6期1362-1367,共6页
Journal of Aerospace Power
关键词
熵层
钝楔
薄激波层
气动加热
气动参数
高超声速
entropy layer
blunt wedge
thin shock layer
aeroheating
aerodynamics parameters
hypersonic
