Effect of transpiration cooling on nozzle heat transfer Academic Article

abstract

• 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.

authors

• Bowersox, Rodney

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

publisher

• American Institute of Aeronautics and Astronautics (AIAA)  Publisher

published in

• Journal of Spacecraft and Rockets  Journal

Digital Object Identifier (DOI)

• 10.2514/3.26784

start page

• 453

end page

• 455

volume

• 33

issue

• 3

URL

• http://dx.doi.org/10.2514/3.26784