Transpiration cooling effects on nozzle heat transfer and performance
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The effects of transpiration cooling on boundary-layer growth, heat transfer, and nozzle performance were investigated. A two-dimensional Mach 2.0 contoured nozzle (Re/m = 5.2 107), with one contoured wall constructed of sintered stainless steel (2.0-m pore size) was tested. Blowing ratios up to 0.51% of the freestream mass flow were tested using high-frequency-response heat flux and pressure instrumentation. Measurements included wall heat flux and static pressure, as well as exit pitot pressure profiles. Shadowgraph photography was used for flow visualization. A reduction in heat transfer of up to 14% was measured for the highest blowing ratio. On the other hand, large increases in the nozzle exit boundary-layer thickness were found. However, blowing had a minimal effect on the nozzle thrust coefficient and specific impulse. In general, this study highlighted the potential beneficial and adverse effects of transpiration cooling on rocket nozzle cooling. 1995 American Institute of Aeronautics and Astronautics, Inc. All right reserved.
Journal of Spacecraft and Rockets
author list (cited authors)
Keener, D., Lenertz, J., Bowersox, R., & Bowman, J.
complete list of authors
Keener, D||Lenertz, J||Bowersox, R||Bowman, J