Hypersonic Shock Wave Boundary Layer Interaction Studies on a Flat Plate at Elevated Surface Temperature
Hypersonic Shock Wave Boundary Layer Interaction Studies on a Flat Plate at Elevated Surface Temperature
复制标题
高表面温度平板上高超声速冲击波边界层相互作用研究
DOI：
10.1007/978-3-319-73180-3_19
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发表时间：
2017
影响因子：
3.3
通讯作者：
Jean
中科院分区：
文献类型：
--
作者：
A. Wagner;J. Schramm;K. Hannemann;R. Whitside;Jean
在德国航空航天中心哥廷根高焓激波风洞（HEG）中，在马赫数为7.4、单位雷诺数为6.65m-1的条件下，对带可偏转襟翼和变表面温度平板模型压缩角处的激波边界层干扰进行了实验研究。本文着重研究了前缘钝度和表面温度的影响。的影响进行了讨论的基础上，表面热通量和表面压力测量以及纹影可视化。该研究证实，进入边界层的状态是至关重要的相互作用。发现前缘钝度的微小变化会影响边界层稳定性，从而影响SBLI。相反，表面加热被发现不稳定的边界层。在不同襟翼偏转角和过渡来流边界层下的试验表明，过渡过程在分离剪切层中完成，导致襟翼上完全紊流再附着。实验的努力是补充的雷诺平均纳维尔-斯托克斯（RANS）计算提供洞察的基本趋势。二维模拟低估了压缩角分离气泡的大小，但定性地反映了实验趋势。壁面加热导致附面层厚度增加，分离泡的范围减小，襟翼上的附面层峰值温度升高。
Experimental shock wave boundary layer interactions (SBLI) at a compression corner of a flat plate model with deflectable flap and variable surface temperature were studied in the High Enthalpy Shock Tunnel Gottingen (HEG) of the German Aerospace Center (DLR) at Mach 7.4 and \({6.65\times 10^6}\,{\text {m}^{-1}}\) unit Reynolds number. The present paper focuses on the effect of the leading edge bluntness and surface temperature. The effects are discussed based on surface heat flux and surface pressure measurements as well as schlieren visualizations. The study confirms that the state of the incoming boundary layer is crucial for the interaction. A small change of the leading edge bluntness was found to affect the boundary layer stability and thus the SBLI. In contrast, surface heating was found to destabilize the boundary layer. Tests at different flap deflection angles and transitional incoming boundary layers revealed that the transition process was completed in the separated shear layer, leading to a fully turbulent reattachment on the flap. The experimental effort is complemented by Reynolds-Averaged Navier–Stokes (RANS) computations providing insights into fundamental trends. The 2D simulations underpredict the size of the separation bubble in the compression corner but qualitatively mirrored the experimental trends. The wall heating resulted in an increased boundary layer thickness, reduced the extent of the separation bubble and elevated the peak boundary layer temperature on the flap.