Heat Transfer Measurements of a Transpiration-Cooled Stagnation Point in Transient Hypersonic Flow

This paper presents a novel experimental technique where infrared thermography is employed to directly measure the surface heat transfer of transpiration-cooled porous material in transient hypersonic flow. Experiments were conducted Oxford High Density Tunnel on flat-faced hemispherical probe at single Mach 7 freestream condition ([Formula: see text]) with nitrogen, air, argon, krypton, and helium injection gases mass flow rates ranging from 0.01 [Formula: text]. Surface measurements extracted by imaging using FLIR A6751 high-speed long-wave camera. Porous alumina was chosen due its favorable thermal properties for analysis very small pore sizes enabling uniform outflow. It found that Stanton number reduction matched within 10% both computational fluid dynamics results correlations.