A numerical study is carried out to investigate the mechanism and assess the parameters of a reverse jet in heat reduction of type IV shock/shock interactions. A hypersonic flow at a Mach number of 8 with a fixed 18.1-deg incident shock is considered. A type IV shock/shock interaction occurs in the front of the blunt leading edge. Compressed air is supersonically injected into the freestream at various jet parameters. The results indicate that a 77% decrease in the peak heat transfer rates can be obtained with a reverse jet placed at the centerline of the blunt body. This study corroborates that the primary physical mechanism of heat reduction of a reverse jet is the transformation of shock interaction from type IV to type III. Moreover, the change of jet parameters, including angle, Mach number, and width, produces different heat reduction effects by influencing the angle between the shear layer of type III interference and the wall tangent.

进行了一项数值研究，以研究 IV 型激波/激波相互作用的热还原中的机制并评估反向射流的参数。考虑具有固定 18.1 度入射激波的马赫数 8 的高超音速流。IV 型冲击/冲击相互作用发生在钝前缘的前面。压缩空气以各种射流参数超音速注入自由气流。结果表明，通过将反向射流放置在钝体的中心线，可以使峰值传热速率降低 77%。这项研究证实，反向射流降热的主要物理机制是激波相互作用从 IV 型到 III 型的转变。此外，射流参数的变化，包括角度、马赫数和宽度，