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Effect of the axial cavity with an opposing high-pressure jet combination in a Mach 6 flow condition
Acta Astronautica ( IF 3.5 ) Pub Date : 2021-01-01 , DOI: 10.1016/j.actaastro.2020.09.021
B. Sudarshan , Srisha M.V. Rao , G. Jagadeesh , S. Saravanan

Abstract Flow control techniques mitigating the aerothermal heating over bodies are essential for long-duration hypersonic flight. The combination technique of a nose cavity with an opposing jet is exhibited promising effects. There is a lacuna of experimental studies on unsteady aspects of the flow and the heat transfer effects within the cavity. In the current study, we investigated the heat transfer variations and nature of shock around a blunt body with a cylindrical and parabolic cavity geometries combined with opposing jet. Experiments are conducted in the hypersonic shock tunnel for a flow Mach number of 6 for an opposing jet pressure ratio of 18. Time-resolved high-speed schlieren imaging and heat flux measurements over the model surface and within the cavity are carried out. The cavity flow is established by verifying the measured heat flux, pressure, and shock oscillation results. The combination technique shows a significant reduction of heat transfer and flow oscillations in comparison to the nose cavity technique. Notably, the parabolic cavity with the opposing jet showed about a 33% reduction of surface heat flux and a 43% reduction in flow oscillations. The substantial increase of heat flux due to the shock interaction is noted on the nose surface for a cylindrical cavity geometry, and such effect was not prevalent in the case of flow with parabolic cavity geometry.

中文翻译:

具有反向高压射流组合的轴向空腔在 6 马赫流动条件下的影响

摘要 减轻物体上的空气热加热的流动控制技术对于长时间的高超音速飞行是必不可少的。鼻腔与反向射流的组合技术显示出良好的效果。关于腔内流动和传热效应的不稳定方面的实验研究存在空白。在当前的研究中,我们研究了具有圆柱形和抛物线形腔几何形状并结合相对射流的钝体周围的传热变化和冲击的性质。实验在高超声速激波隧道中进行,流动马赫数为 6,反向射流压力比为 18。在模型表面和空腔内进行时间分辨高速纹影成像和热通量测量。通过验证测量的热通量、压力和冲击振荡结果来建立腔体流动。与鼻腔技术相比,该组合技术显着减少了传热和流动振荡。值得注意的是,具有相反射流的抛物线腔显示表面热通量减少约 33%,流动振荡减少 43%。在圆柱腔几何形状的鼻表面上注意到由于冲击相互作用而导致的热通量的显着增加,并且这种影响在具有抛物线腔几何形状的流动的情况下并不普遍。带有相反射流的抛物线腔显示表面热通量减少了约 33%,流动振荡减少了 43%。在圆柱腔几何形状的鼻表面上注意到由于冲击相互作用而导致的热通量的显着增加,并且这种影响在具有抛物线腔几何形状的流动的情况下并不普遍。带有相反射流的抛物线腔显示表面热通量减少了约 33%,流动振荡减少了 43%。在圆柱腔几何形状的鼻表面上注意到由于冲击相互作用而导致的热通量的显着增加,并且这种影响在具有抛物线腔几何形状的流动的情况下并不普遍。
更新日期:2021-01-01
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