Dataset
Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer - Dataset
- Documentation:
- 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.
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Authors/Creators
+ Engineering and Physical Sciences Research Council
More from this funder
- Funding agency for:
- McGilvray, M
- Grant:
- EP/P000878/1
- Publisher:
- University of Oxford
- Publication date:
- 2022
- DOI:
- Language:
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English
- Pubs id:
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1481193
- Local pid:
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pubs:1481193
- Deposit date:
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2022-11-28
- ARK identifier:
Terms of use
- Copyright date:
- 2022
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