This work focuses on the heat flux characteristics of a hypersonic blunt body with a tangential Mach 3 supersonic cooling film. Experiments were carried out with main flow’s Mach numbers of 6, 7, and 8; total pressure of 15 MPa, and total temperature of 2600 K. The wall surface heat flux was measured under different cooling film pressures. Nanoparticle-based planar laser scattering was used to visualize the flowfield. Results showed that cooling film can effectively reduce surface heat flux of the test model, but the cooling efficiency was continuously weakened along the flow direction; a cooling film with a higher mass flow rate was more effective in protecting the model’s surface; the instability of the boundary layer and the mixing layer accelerated heat exchange between the mainstream, the cooling film, and the model surface.

这项工作着眼于具有切向马赫3超音速冷却膜的高超音速钝体的热通量特性。在主流的马赫数分别为6、7和8的情况下进行了实验；总压力为15 MPa，总温度为2600K。在不同冷却膜压力下测量壁表面热通量。基于纳米粒子的平面激光散射用于可视化流场。结果表明，冷却膜可以有效降低试验模型的表面热通量，但冷却效率沿流动方向不断减弱；质量流量较高的冷却膜在保护模型表面方面更有效；边界层和混合层的不稳定性加速了主流，冷却膜和模型表面之间的热交换。