Effect of transpiration cooling on nozzle heat transfer Academic Article uri icon


  • 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.

published proceedings

  • Journal of Spacecraft and Rockets

author list (cited authors)

  • Chen, F., Bowman, W. J., & Bowersox, R.

citation count

  • 2

complete list of authors

  • Chen, F||Bowman, WJ||Bowersox, R

publication date

  • May 1996