摘要
运用激波管风洞在Ｒ＿（ｅ∞／ｍ＝３×１０￣７，Ｍ＿∞＝０．７３２－０．８１７范围内，在厚度比为１２％的圆弧翼型半模型和厚度比为１４％的超临界翼型半模型上，对被动控制现象及其若干规律进行了实验研究。结果表明，不同空腔深度的开孔壁和导管连通壁均可对壁面激波与边界层的相互作用实现被动控制，使得沿以上两种模型表面的马赫数峰值、逆压力梯度和激波强度明显减小。这对于飞行器将起到减阻作用，如将这一原理和方法用于超、跨声速压气机内激波与边界层相互作用的控制，将提高压气机的效率和工作的稳定性。
This work has been done in a shock tunnel,in the range M_∞=0.732 ～ 0.817and Re_∞=3 × 10￣7,on different half models:circular arc aerofoils with 12%thickness ratioand supercritical aerofoils with 14%thickness ratio。 The results show that:in comparisonwith solid wall of the model,the porous walls with cavity deepness 1mm or 3mm,and thewall with conduit tubes can reduce the peak of Much Number,adverse pressure gradient, andthe strength of shock wave That means passive control can reduce the drag of an aircraftand can increase the stability of flow。 The different ways of passive control above-mentionedhave been compared。
出处
《力学学报》
EI
CSCD
北大核心
1995年第5期523-535,共13页
Chinese Journal of Theoretical and Applied Mechanics
关键词
激波
边界层
被动控制
跨音速流动
transonic flow, interaction between shock wave and boundary layer,passivecontrol
