Aerodynamic Heating from Compression Corner Interactions in Hypersonic Flow

Abstract

Localized thermal loads on hypersonic vehicles are often caused by geometric features that intensify compression and shock interactions. To better quantify this phenomenon, this study looks into the heating generated by compression corner shock interactions on a cone-flare model in Mach 6 flow. Experiments were conducted in a high-temperature Ludwieg tube hypersonic wind tunnel using various flare angles which depict a relationship between the local shock structures and surface heat flux. Temperature-sensitive paint applied on the surface of the cone-flare model spatially mapped heating measurements, with brightness changes recorded by a high-speed Phantom camera and converted to transient heat-flux data. Concurrently, Schlieren imaging captured the shock structures, enabling direct comparison between shock-reattachment locations and regions of elevated heating. Results show a clear increase in surface heating near the flare junction corresponding to the compressive shock structures. These findings highlight how compressive features such as control surfaces can drive localized thermal loads, informing improved thermal protection strategies for future hypersonic vehicle designs.