Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset
Two-dimensional simulations of transpiration cooling in a laminar, hypersonic boundary layer were performed using the thermochemical implicit nonequilibrium algorithm (TINA): a Navier–Stokes solver. Coolant concentration and heat flux results are compared to data obtained from laminar transpiration...
| Main Authors: | , , , |
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| Format: | Dataset |
| Language: | English |
| Published: |
University of Oxford
2022
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| _version_ | 1797108354518089728 |
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| author | Ifti, H S Hermann, T McGilvray, M Merrifield, J |
| author_facet | Ifti, H S Hermann, T McGilvray, M Merrifield, J |
| author_sort | Ifti, H S |
| collection | OXFORD |
| description | Two-dimensional simulations of transpiration cooling in a laminar, hypersonic boundary layer were performed using the thermochemical implicit nonequilibrium algorithm (TINA): a Navier–Stokes solver. Coolant concentration and heat flux results are compared to data obtained from laminar transpiration cooling experiments conducted in the Oxford High Density Tunnel employing a flat-plate geometry at Mach 7. TINA successfully predicts the mixing rate at the wall as a function of the streamwise direction for all blowing ratios. The simulations are more successful in predicting the mixing downstream of the injector as compared to the mixing on the injector: especially at low blowing ratios. A collapse of the thermal effectiveness values calculated from TINA simulation data is achieved, which agrees with laminar correlations within an absolute value of ±10%. It is shown that, when the concentration effectiveness is close to one at the injector, the temperature gradient becomes negative at locations immediately downstream of the injector, resulting in a negative heat flux. The acceleration of the coolant in the streamwise direction downstream promotes dissipation of energy, which results in a reduction in the temperature of the coolant, and thereby induces a negative temperature gradient close to the injector. |
| first_indexed | 2024-03-07T07:28:01Z |
| format | Dataset |
| id | oxford-uuid:db822785-eebe-4f4c-917b-c082ee3aa530 |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-07T07:28:01Z |
| publishDate | 2022 |
| publisher | University of Oxford |
| record_format | dspace |
| spelling | oxford-uuid:db822785-eebe-4f4c-917b-c082ee3aa5302022-11-30T19:06:01ZNumerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - DatasetDatasethttp://purl.org/coar/resource_type/c_ddb1uuid:db822785-eebe-4f4c-917b-c082ee3aa530EnglishHyrax DepositUniversity of Oxford2022Ifti, H SHermann, TMcGilvray, MMerrifield, JTwo-dimensional simulations of transpiration cooling in a laminar, hypersonic boundary layer were performed using the thermochemical implicit nonequilibrium algorithm (TINA): a Navier–Stokes solver. Coolant concentration and heat flux results are compared to data obtained from laminar transpiration cooling experiments conducted in the Oxford High Density Tunnel employing a flat-plate geometry at Mach 7. TINA successfully predicts the mixing rate at the wall as a function of the streamwise direction for all blowing ratios. The simulations are more successful in predicting the mixing downstream of the injector as compared to the mixing on the injector: especially at low blowing ratios. A collapse of the thermal effectiveness values calculated from TINA simulation data is achieved, which agrees with laminar correlations within an absolute value of ±10%. It is shown that, when the concentration effectiveness is close to one at the injector, the temperature gradient becomes negative at locations immediately downstream of the injector, resulting in a negative heat flux. The acceleration of the coolant in the streamwise direction downstream promotes dissipation of energy, which results in a reduction in the temperature of the coolant, and thereby induces a negative temperature gradient close to the injector. |
| spellingShingle | Ifti, H S Hermann, T McGilvray, M Merrifield, J Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset |
| title | Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset |
| title_full | Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset |
| title_fullStr | Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset |
| title_full_unstemmed | Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset |
| title_short | Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset |
| title_sort | numerical simulation of transpiration cooling in a laminar hypersonic boundary layer dataset |
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