摘要
以超燃冲压发动机等截面隔离段内部流动阻力特性为研究背景,以数值模拟和实验测量为研究手段,研究马赫数2.5来流条件下,平板流动和带激波反射流动条件下的壁面摩擦阻力。实验测量得到了超声速流动下的壁面摩擦阻力。研究发现,当激波反射形成局部微小分离时,激波和边界层的相互作用使得分离区下游的壁面剪切应力恢复为比分离区上游稍高水平。存在激波反射时,壁面总的摩擦阻力略大于无激波时的平板流动。
Skin friction drags of flow with incoming Mach number of 2.5 on an insulated flat plate with and without shock impingement were studied through numerical simulations and experimental measurements. It is for the requirement of flow drag characteristics in constant section isolator of seramjet. Skin friction drags were measured in supersonic flow. When shock reflected on the wall and induced flow separating in small region, the interaction between shock and turbulent boundary layer made the skin friction level in downstream of interaction higher than that in the upstream. If shock reflection occurred, the total friction drag of the wall was greater than that without shock.
出处
《空气动力学学报》
EI
CSCD
北大核心
2009年第1期124-128,共5页
Acta Aerodynamica Sinica
基金
国家863-702专题子项目
基金编号2005AA723020
