Oz Furkan, Kara Kursat
School of Mechanical and Aerospace Engineering, Oklahoma State University, Stillwater, OK, 74078, USA.
Sci Rep. 2024 Jul 10;14(1):15928. doi: 10.1038/s41598-024-66867-4.
This study investigates a novel method to control hypersonic boundary layer transition using a combined local cooling and local metasurface treatment. The method's effectiveness was investigated on a 5-degree half-angle blunt wedge with a nose radius of 0.0254 mm at a freestream Mach number of 6.0 using direct numerical simulations and linear stability theory. We explored four cases: (i) adiabatic baseline case, (ii) locally cooled case, (iii) local metasurface case, and (iv) combined local cooling-local metasurface case. Results showed that the combined local cooling-local metasurface treatment significantly reduced both wall pressure disturbance amplitude and the density perturbation amplitude around the sonic line, indicating a potential for controlling hypersonic boundary layer transition. In the local cooling-local metasurface case, the disturbance amplitude at the end of the computational domain was 270 times lower than the baseline case. The study also examined the impact of Reynolds numbers, ranging from 25.59 million per meter to 32.80 million per meter. Unsteady simulations revealed that the Reynolds number had a negligible effect on the local cooling-local metasurface performance, indicating that the proposed method applies to a wide range of flight conditions.
本研究探讨了一种结合局部冷却和局部超表面处理来控制高超声速边界层转捩的新方法。使用直接数值模拟和线性稳定性理论，在自由流马赫数为6.0、头部半径为0.0254毫米的5度半角钝楔上研究了该方法的有效性。我们探讨了四种情况：（i）绝热基线情况，（ii）局部冷却情况，（iii）局部超表面情况，以及（iv）局部冷却 - 局部超表面组合情况。结果表明，局部冷却 - 局部超表面组合处理显著降低了声线周围的壁面压力扰动幅度和密度扰动幅度，表明具有控制高超声速边界层转捩的潜力。在局部冷却 - 局部超表面情况下，计算域末端的扰动幅度比基线情况低270倍。该研究还考察了雷诺数从每米2559万到每米3280万的影响。非定常模拟表明，雷诺数对局部冷却 - 局部超表面性能的影响可忽略不计，这表明所提出的方法适用于广泛的飞行条件。
