Hybrid propulsion concepts required development of nozzle system capable of withstanding gas temperatures in excess of 6200 F for burn times longer than 30 sec; tungsten nozzle insert systems provided best operation; heat transfer rates were lower with tungsten metal systems than for unmodified tungsten indicating that transpiration cooling was being realized; laboratory program subjecting infiltrated tungsten samples to plasma-arc heat source; technique offers excellent nozzle system for long time firing durations in hybrid and solid propellant rockets.
Transpiration cooling with liquid metals
AIAA J
AIAA Journal ; 1 , n 1
1963
7 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
TRANSPIRATION COOLING WITH LIQUID METALS
AIAA | 1963
|Transpiration Cooling Using Liquid Water
AIAA | 2009
|Transpiration Cooling Using Liquid Water
British Library Conference Proceedings | 2007
|Transpiration Cooling Using Liquid Water
AIAA | 2007
|