Numerical investigation on the thermal protection mechanism for blunt body with forward-facing cavity

Numerical investigation on the thermal protection mechanism for blunt body with forward-facing cavity
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前向腔钝头体热防护机理的数值研究

DOI:
10.1007/s11431-016-6015-4
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发表时间:
2016-01
期刊:
Science in China - Series E: Technological Sciences
影响因子:
--
通讯作者:
Jiang ZongLin
Jiang ZongLin
中科院分区:
其他
文献类型:
--
作者:
Li XinDong;Hu ZongMin;Jiang ZongLin

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利用标准的高超声速弹道模型(HB-2)进行了数值试验,研究了前向空腔对气动加热的影响。本文提出了一种利用在亚音速区被动产生的流动扰动来削弱脱体激波的一般概念。主要研究了激波形状与靶距、表面热流密度与压力、流场特征及冷却机理等几个方面。数值计算结果表明,随着空腔长径比的增大,冲击波强度增大,射距增大。有趣的是,第一次观察到与深空泡相关联的分离激波的隆起结构。凹头附近的局部表面热流和压力分别比基准模型驻点处的低得多。此外,表面热量和压力的减少都与L/D比成正比。在尖唇附近或深腔底壁上可能出现负加热现象。如果L/D比超过0.7,脱体冲击表现为自持振荡,可以将其称为冷却机制。
Numerical experiments are carried out using the standard hypersonic ballistic-type model (HB-2) to investigate the effect of forward-facing cavity on the aerodynamic heating. A general concept is proposed which utilizes the flow disturbances generated passively in the nosed subsonic region to weaken the detached shock wave. Several aspects are mainly studied, including shock shape and standoff distance, surface heat flux and pressure, flowfield feature and cooling mechanism. The numerical results indicate that shock strength and standoff distance increase with an increase in theL/Dratio of the cavity. Interestingly, a bulge structure of the detached shock associated with a deep cavity is observed for the first time. Local surface heat flux and pressure around the concave nose are much lower respectively than those at the stagnation point of the baseline model. In addition, both surface heat and pressure reductions are proportional to theL/Dratio. A negative heating phenomenon may occur in the vicinity of a sharp lip or on the base wall of a deep cavity. If theL/Dratio exceeds 0.7, the detached shock appears as a self-sustained oscillation which can be referred to as the cooling mechanism.
DOI: 10.2514/3.25513
发表时间: 1993-06
影响因子: 1.6
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发表时间: 2007-03
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