Effect of transpiration cooling on nozzle heat transfer
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The effect of transpirations cooling at various blowing ratios on turbulent heat transfer are investigated on a two-dimensional contoured nozzle. Overall, the heat transfer rate is shown to be significantly reduced by transpiration cooling. A 40% reduction is measured for a local blowing ratio of 1.17%. The present two-dimensional results have indicated that transpiration cooling has the potential to be an effective means of rocket nozzle cooling.
Journal of Spacecraft and Rockets
author list (cited authors)
Chen, F., Bowman, W. J., & Bowersox, R.
complete list of authors
Chen, F||Bowman, WJ||Bowersox, R