A supersonic annular supersonic nozzle was used to protect a slender cone from aerodynamic heating at angle of attack (AoA). Experiments were carried out in a Mach 6 wind tunnel. Temperature-sensitive paint (TSP) was used to measure surface temperature change of the cone body; nanoparticle-based planar laser scattering (NPLS) was used to visualize the flow field; oil flow was utilized to monitor surface flow of the cone. Results showed that cooling film can obviously decrease surface heating load in present cases; the coolant layer was able cover a relatively long distance along the model's surface than most other cooling solutions. AoA caused obvious transverse flow on the surface, and it produced much difference heating load between different sides of the cone body. Although the cooling film can mitigate the transverse flow, the windward side was still the hardest part to cool. (C) 2022 Elsevier Masson SAS. All rights reserved.
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