董昊, 张旭东, 刘是成, 等. 高超声速逆向喷流数值模拟和风洞试验[J]. 空气动力学学报, 2022, 40(4): 101−109. doi: 10.7638/kqdlxxb-2021.0240
引用本文: 董昊, 张旭东, 刘是成, 等. 高超声速逆向喷流数值模拟和风洞试验[J]. 空气动力学学报, 2022, 40(4): 101−109. doi: 10.7638/kqdlxxb-2021.0240
DONG H, ZHANG X D, LIU S C, et al. Numerical and experimental study on opposing jet in hypersonic flow[J]. Acta Aerodynamica Sinica, 2022, 40(4): 101−109. doi: 10.7638/kqdlxxb-2021.0240
Citation: DONG H, ZHANG X D, LIU S C, et al. Numerical and experimental study on opposing jet in hypersonic flow[J]. Acta Aerodynamica Sinica, 2022, 40(4): 101−109. doi: 10.7638/kqdlxxb-2021.0240

高超声速逆向喷流数值模拟和风洞试验

Numerical and experimental study on opposing jet in hypersonic flow

  • 摘要: 作为一种主动流动控制技术,逆向喷流因其在降低气动热方面的广阔前景而成为研究热点。为探索逆向喷流流动控制技术对高超声速飞行器降热的影响规律及相关机理,对半球体钝体模型进行了不同来流和喷流条件下的数值模拟和风洞试验研究,得到了模型表面的流场和斯坦顿数分布,并对数值模拟和风洞试验结果进行了相互校验。结果表明:逆向喷流产生的降热效果是喷流气体回流和喷流推离头部脱体激波共同作用的结果;在相同来流马赫数下,逆向喷流降热效果随喷流压比的增大而更加显著;在相近喷流压比条件下,来流马赫数越大,逆向喷流降热效果越好。

     

    Abstract: As an active flow control technology, the opposing jet has become a research hotspot due to its broad prospect in reducing aerodynamic heat. In order to explore the heat flux reduction law and related mechanism of opposing jet flow control for hypersonic vehicles, a hemispherical bluff body model was studied by numerical simulations and wind tunnel experiments under different freestream and opposing jet conditions. The flow field and Stanton number distribution on the model surface were obtained, and both numerical and experimental data were verified against each other. The results suggest that, the heat flux reduction effect of the opposing jet is the consequence of a combined action of the jet backflow and the jet pushing away the front shockwave from the head. At a fixed Mach number, the heat flux reduction effect of opposing jet becomes more obvious with the increase of the jet pressure ratio; while under the condition of a similar jet pressure ratio, better heat flux reduction effect by the opposing jet can be achieved at higher Mach numbers.

     

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