Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer
| Autor: | Ifti, HS, Hermann, T, McGilvray, M, Merrifield, J |
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| Rok vydání: | 2022 |
| Předmět: | |
| Zdroj: | Journal of Spacecraft and Rockets. 59:1726-1735 |
| ISSN: | 1533-6794 0022-4650 |
| Popis: | 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. |
| Databáze: | OpenAIRE |
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