平板空气舵干扰区烧蚀凹陷对热环境影响

针对高速飞行条件下空气舵干扰区烧蚀产生的局部凹陷对气动加热的影响问题,建立了平板-空气舵流动模型,针对典型高速飞行状态,采用高温热化学非平衡数值模拟,研究了空气舵缝隙区的流动结构和气动加热规律,并对舵缝干扰区的烧蚀外形进行了模化,分析了干扰区烧蚀凹陷对流动结构和气动加热的影响,结果表明:烧蚀凹陷改变了干扰区压力分布规律,降低了沿展向压力梯度,从而抑制了边界层的横向流动和厚度减薄效应,使得干扰区热流降低,且热流降低量值与烧蚀凹陷深度呈正相关,凹陷深度为5 mm时干扰区热流降低量达到28.9%。 

Effect on heating environment of ablation recession in plate-rudder interaction region

The effect of the ablation recession on the heat flux near a rudder gap interaction region was studied. High temperature thermal-chemical non-equilibrium numerical simulation was conducted for a plate-rudder configuration under typical hypersonic flow condition. The flow and aeroheating mechanism was analyzed for the rudder gap interaction region. The shape change caused by ablation recession was modeled and its effect on the flow structure and aeroheating mechanism was studied. Results indicated that the ablation recession changed the pressure distribution in the interaction region and decreased the spanwise pressure gradient, which inhibited the thickness reduction of the boundary layer by the cross-flow, and led to decrease of the heat flux in the interaction region. This heat flux decrease value was intensified as the ablation recession depth increased, which can reach 28.9% at a 5 mm recession depth.