Oxidation Response of Transpiration Cooled ZrB2 on a Hypersonic Stagnation Point - Dataset
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...
| Main Authors: | , , |
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| Format: | Dataset |
| Language: | English |
| Published: |
University of Oxford
2022
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| Summary: | 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 mm and 0.075 mm, respectively. |
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