高超声速平板/空气舵热环境数值模拟研究

Numerical simulation of aerodynamic heating environment of a hypersonic plate/rudder configuration

针对高超声速平板/空气舵模型开展了热环境数值模拟研究,重点分析了舵偏角δr、舵缝高度h和边界层流态对缝隙内舵轴及干扰区热环境的影响规律。研究结果表明:零舵偏状态缝隙内气流速度为亚声速,热环境可以忽略;舵面偏转时,缝隙入口气流速度和压力显著增大,在δr=5°～15°范围内,舵轴及干扰区热环境随舵偏近似线性增长;舵轴及干扰区热流随h增大呈现先上升后缓慢下降的趋势,h从5 mm增大到7mm时,舵轴热环境增加超过1倍;边界层流态对空气舵缝隙内热环境影响很大,在15°舵偏条件下,层流状态舵轴及干扰区热环境约是湍流的3～5倍,这是因为层流边界层较薄,缝隙内流速更高。

This article presents a numerical study to investigate aerodynamic heating environments of a hypersonic plate/rudder configuration. In particular, the effects of the deflection angle δ r , gap displacement h, and boundary layer flow pattern on aerodynamic heating environment of the rudder shaft as well as its interaction region were analyzed in detail. The analysis show that the heating environment in the gap is negligible at 0° deflection angle due to the subsonic flow. However, the rudder deflection results in high speed and high pressure flow inside the gap, the thermal loads of the rudder shaft, and its interaction region almost linearly increase with increasing δ r between 5° and 15°. The heating flux of the rudder shaft and its interaction region increase firstly and then decrease gradually with the increasing h . The heat flux of h =7 mm is nearly two times of that of h =5 mm. In addition, the flow pattern of the boundary layer exerts a significant influence on the heat flux in the gap. In full laminar case, the thermal loads of the rudder shaft and its interaction region are three to five times of those within the full turbulent case under the condition of δ r =15°. This is because the thinner boundary layer of laminar flow results in high speed flow in the gap.