This work presents the oxidation response of a transpiration-cooled hypersonic stagnation point made of porous . 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 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 hypersonic vehicle with a 3 mm nose radius is found to exceed 0.94 mm with no mass injection. It is shown that nitrogen and helium injection at a blowing parameter of 0.6 can reduce the recession to 0.13 and 0.075 mm, respectively.
Oxidation Response of Transpiration-Cooled on a Hypersonic Stagnation Point
Journal of Spacecraft and Rockets ; 59 , 5 ; 1486-1495
2022-05-12
10 pages
Article (Journal)
Electronic Resource
English
Stagnation Point Probes in Hypersonic Flow
British Library Conference Proceedings | 2018
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