Oxidation response of transpiration-cooled ZrB2 on a hypersonic stagnation point
This work presents the oxidation response of a transpiration-cooled hypersonic stagnation point made of porous ZrB2. 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 reces...
| Auteurs principaux: | , , |
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| Format: | Journal article |
| Langue: | English |
| Publié: |
American Institute of Aeronautics and Astronautics
2022
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| Résumé: | This work presents the oxidation response of a transpiration-cooled hypersonic stagnation point made of porous ZrB2. 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 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.
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