A hypersonic shock wave/laminar boundary-layer interaction over a canonical $25{-}55^{\circ }$ double-cone configuration is numerically investigated. A moderate-enthalpy flow of $5~\text{MJ}~\text{kg}^{-1}$ with a Mach number of 9.87 and a unit Reynolds number of $1.5\times 10^{5}~\text{m}^{-1}$ is considered. Special emphasis is given to the influence of leading-edge bluntness. The results indicate that the double-cone flow is insensitive to small bluntness in terms of shock structures, separation region sizes and surface pressure and heat flux distributions. A critical nose radius is observed, beyond which the separation bubble grows dramatically. The numerical data are analysed and interpreted based on a triple-deck formulation. It is shown that the sudden change in flow features is mainly caused by pressure overexpansion on the first cone due to leading-edge bluntness, such that the skin friction upstream of the separation is significantly reduced and the upstream pressure can no longer resist the large adverse pressure gradient induced by shock impingement. An estimation of the critical radius is established based on the pressure correlations of Blick & Francis (AIAA J., vol. 4 (3), 1966, pp. 547–549) for spherically blunted cones. Simulations at a higher enthalpy with the presence of both vibrational relaxation and air chemistry show a similar trend with increasing nose radius. The proposed criterion agrees well with the experimental observations.

数值研究了规范的 $ 25 {-} 55 ^ {\ circ} $ 双锥配置上的高超声速冲击波/层状边界层相互作用。 $ 5〜\ text {MJ}〜\ text {kg} ^ {-1} $ 的中等焓流，马赫数为9.87，单位雷诺数为 $ 1.5 \乘以10 ^ {5}〜\ text {m } ^ {-1} $ 被认为。特别强调前沿钝性的影响。结果表明，在冲击结构，分离区域大小，表面压力和热通量分布方面，双锥流对小钝性不敏感。观察到临界鼻半径，超过该临界半径，分离气泡会急剧增长。数值数据基于三层公式进行分析和解释。结果表明，流动特性的突然变化主要是由于前沿钝化导致第一锥体上的压力过度膨胀所致，因此分离上游的皮肤摩擦明显减小，上游压力不再能够抵抗较大的不利影响。冲击引起的压力梯度。AIAA J.，第 4（3），1966，pp。547–549）球形钝锥。在同时具有振动弛豫和空气化学作用的情况下，在较高的焓下进行的模拟显示出随着鼻半径的增加而出现的类似趋势。提出的标准与实验观察非常吻合。