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李帅, 姜振华, 张珊, 尹同, 阎超. 局部凸起在V形钝前缘模型中的降热特性研究. 力学学报, 2024, 56(2): 138-150. DOI: 10.6052/0459-1879-23-409
引用本文: 李帅, 姜振华, 张珊, 尹同, 阎超. 局部凸起在V形钝前缘模型中的降热特性研究. 力学学报, 2024, 56(2): 138-150. DOI: 10.6052/0459-1879-23-409
Li Shuai, Jiang Zhenhua, Zhang Shan, Yin Tong, Yan Chao. Investigation on the heat flux reduction characteristics of the local bulges in the V-shaped blunt leading edge. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(2): 138-150. DOI: 10.6052/0459-1879-23-409
Citation: Li Shuai, Jiang Zhenhua, Zhang Shan, Yin Tong, Yan Chao. Investigation on the heat flux reduction characteristics of the local bulges in the V-shaped blunt leading edge. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(2): 138-150. DOI: 10.6052/0459-1879-23-409

局部凸起在V形钝前缘模型中的降热特性研究

INVESTIGATION ON THE HEAT FLUX REDUCTION CHARACTERISTICS OF THE LOCAL BULGES IN THE V-SHAPED BLUNT LEADING EDGE

  • 摘要: 三维内转式进气道的唇口结构通常存在复杂的激波干扰及严酷的气动热载荷, 严重威胁高超声速飞行器的性能与安全. 在6.0马赫的高超声速流动中, 以V形钝前缘模型为研究对象, 设计了局部凸起的被动流动控制降热方案. 采用数值模拟手段, 首先研究了局部凸起方案的降热能力以及降热原理, 然后初步优化了局部凸起的位置、高度以及宽度等关键设计参数, 最后分析了优化后的局部凸起方案的攻角、侧滑角及马赫数的适用性. 研究结果表明: 上游凸起边缘形成的斜激波与主马赫反射结构形成的透射激波发生干扰, 能够减弱其冲击壁面的强度, 实现降热的目的; 驻点凸起通过改变超声速射流的对撞角度, 能够降低其对撞的强度, 实现降热的目的. 原始方案的降热能力约为37.75%, 在对局部凸起的关键设计参数进行初步优化后, 优化方案的降热能力将提升至44.60%. 设计工况下的优化方案具有良好的攻角适用性, 而高度可变的优化方案可以较好地适用于有侧滑角及高马赫数的流动. 在研究范围内, 高度可变的优化局部凸起方案的降热能力均高于20%.

     

    Abstract: Complex shock interaction structures and severe aerothermal heating loads are usually encountered on the lips of the three-dimensional inward-turning inlet, which seriously threatens the performance and safety of the hypersonic flight vehicle. The passive heat flux reduction scheme with the local bulge is designed based on the simplified model of the V-shaped lip, the V-shaped blunt leading edge. By performing numerical simulations, the heat flux reduction ability and the heat flux reduction principle of the local bulge scheme are researched at Mach number of 6.0. Then, the key design parameters of the scheme, which include the position, the height, and the width of the local bulge, are preliminarily optimized. Finally, the applicability of the optimized scheme in terms of attack angle, sideslip angle, and Mach number is analyzed. The oblique shocks formed at the edges of the upstream bulge interact with the transmitted shock formed by the primary Mach reflection structure, which can weaken the intensity of the transmitted shock impinging on the wall and achieve the purpose of heat flux reduction. By changing the collision angle of the supersonic jets, the stagnation bulge can reduce the collision intensity of the jets and achieve the purpose of heat flux reduction as well. The heat flux reduction ability of the original local bulge scheme is about 37.75%. After preliminarily optimizing the key design parameters of the local bulge scheme, the heat flux reduction ability of the optimized local bulge scheme can be increased to 44.60%. The optimized scheme under design condition has excellent applicability of attack angle. Meanwhile, the optimized scheme with changeable height can be well applied to the flow with sideslip angles or high freestream Mach numbers. Within the research scope of this work, the heat flux reduction ability of the optimized local bulge scheme with changeable height is higher than 20%.

     

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