Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer
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: | , , , |
|---|---|
| Format: | Journal article |
| Language: | English |
| Published: |
American Institute of Aeronautics and Astronautics
2022
|
| _version_ | 1797107704023482368 |
|---|---|
| author | Ifti, HS Hermann, T McGilvray, M Merrifield, J |
| author_facet | Ifti, HS Hermann, T McGilvray, M Merrifield, J |
| author_sort | Ifti, HS |
| 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 | 2024-03-07T07:19:42Z |
| format | Journal article |
| id | oxford-uuid:53bf6517-aaa4-41cf-91ab-13cc55674ac7 |
| institution | University of Oxford |
| language | English |
| last_indexed | 2024-03-07T07:19:42Z |
| publishDate | 2022 |
| publisher | American Institute of Aeronautics and Astronautics |
| record_format | dspace |
| spelling | oxford-uuid:53bf6517-aaa4-41cf-91ab-13cc55674ac72022-09-27T08:16:35ZNumerical simulation of transpiration cooling in a laminar hypersonic boundary layerJournal articlehttp://purl.org/coar/resource_type/c_dcae04bcuuid:53bf6517-aaa4-41cf-91ab-13cc55674ac7EnglishSymplectic ElementsAmerican Institute of Aeronautics and Astronautics2022Ifti, HSHermann, 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, HS Hermann, T McGilvray, M Merrifield, J Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| title | Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| title_full | Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| title_fullStr | Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| title_full_unstemmed | Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| title_short | Numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| title_sort | numerical simulation of transpiration cooling in a laminar hypersonic boundary layer |
| work_keys_str_mv | AT iftihs numericalsimulationoftranspirationcoolinginalaminarhypersonicboundarylayer AT hermannt numericalsimulationoftranspirationcoolinginalaminarhypersonicboundarylayer AT mcgilvraym numericalsimulationoftranspirationcoolinginalaminarhypersonicboundarylayer AT merrifieldj numericalsimulationoftranspirationcoolinginalaminarhypersonicboundarylayer |