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 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 dir...Expand abstract
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- Copyright © 2022 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
This is the accepted manuscript version of the article. The final version is available from American Institute of Aeronautics and Astronautics at https://doi.org/10.2514/1.A35325
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