Effect of transpiration cooling on nozzle heat transfer

被引：3

作者：

Chen, F

Bowman, WJ

Bowersox, R

机构：

[1] U.S. Air Force Inst of Technology, Wright-Patterson Air Force Base, OH

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 1996年 / 33卷 / 03期

关键词：

D O I：

10.2514/3.26784

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

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.

引用

页码：453 / 455

页数：3

共 7 条

[1]

BARTZ DR, 1957, JET PROPULSION, V27, P49

[2] REDUCTION OF DATA FROM THIN-FILM HEAT-TRANSFER GAGES - A CONCISE NUMERICAL TECHNIQUE [J].