摘要
论文详细分析了气相爆轰波在斜劈上Mach反射后的流场 .根据胞格结构的烟迹记录 ,得到了爆轰波Mach反射时三波点迹线与楔面的夹角Χ (也称激波角 ,shock shockangle)与楔角Θ的定量关系 ,依此推算出爆轰波绕射楔块时从规则反射 (normalreflection)向Mach反射转变的临界角范围 .论文也分析了影响Χ角和Mach杆后压力的主要因素 .该结果有助于更深入了解爆轰波的本质 ,也为数值模拟气相爆轰波在障碍物上Mach反射现象提供了可靠的对照依据 .
The experimental evidence of Mach reflection of gaseous detonation waves diffracting an obstacle are presented in our paper. A detailed quantitative analysis of the flow field that forms behind Mach reflection is presented in this paper. According to the recorded cellular structure, the relationship between shock shock angles (the angle formed by trajectory of triple point and the slope of wedge) and wedge angles can be determined. Therefore the range of critical angle, on which the regular reflection is transferred into Mach reflection when detonation wave is diffracting on a wedge, can be estimated reasonably. The main factor that determines the shock shock angle and the pressure behind the Mach stem is also analysed here. These results will further our understanding of the nature of detonation, in addition to providing the reference for comparison when making numerical simulation for this phenomenon.
基金
国家自然科学基金!(19872 0 6 8)资助项目
