Oxidation Response of Transpiration-Cooled ZrB2 on a Hypersonic Stagnation Point

Abstract

This work presents the oxidation response of a transpiration cooled hypersonic stagnation point made of porous ZrB 2 . Low order models are used to calculate the surface temperature and oxygen concentration for a given flight condition. An analytical material oxidation model computes the surface recession and oxide layer thickness. A 500 s steady state trajectory at 44 km altitude and 3.6 km/s velocity is found to lead to 2.2 mm recession of the 3 mm nose radius. A constant mass injection at a blowing parameter of 0.6 reduces the recession to just 0.21 mm. The displacement of freestream oxygen by transpiration cooling has a significant effect on oxidation. Not accounting for the displacement of oxygen at the surface would increase the recession by up to 197%. The recession along the transient trajectory of an envisioned

Materials design for hypersonics

“…Still ablative thermal protection systems do not favor re-usability 31 . In contrast, hot structures, heat pipes, and active thermal management systems (enabled by additive manufacturing) have dominated research efforts for candidate materials and system designs [32][33][34][35][36][37][38][39] .…”