An Analysis of Nuclear-Rocket Nozzle Cooling
National Aeronautics and Space Administration, 1960 - Aerodynamics, Supersonic - 26 pages
A nuclear-rocket regenerative-cooling analysis was conducted over a range of reactor power of 46 to 1600 megawatts and is summarized herein. Although the propellant (hydrogen) is characterized by a large heat-sink capacity, an analysis of the local heat-flux capability of the coolant at the nozzle throat indicated that, for conventional values of system pressure drop, the cooling capability was inadequate to maintain a selected wall temperature of 1440 R. Several techniques for improving the cooling capability were discussed, for example, high pressure drop, high wall temperature, refractory wall coatings, thin highly conductive walls, and film cooling. In any specific design a combination of methods will probably be utilized to achieve successful cooling.
4 pages matching methods will probably in this book
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1600 megawatts ANALYSIS OF NUCLEAR-ROCKET analysis was conducted capability was inadequate convective heat transfer coolant Mach number cooling capability cooling margin Copies obtainable D-482 National Aeronautics Daniel Bachkin design a combination drop and limiting film cooling ful cooling gamma heating heat transfer heat-flux capability heat-transfer high pressure drop high wall temperature highly conductive walls improving the cooling large heat-sink capacity limiting wall temperature margin were discusced Medeiros methods will probably NASA TECHNICAL NOTE NASA TN nozzle length nozzle throat indicated nozzle wall NUCLEAR-ROCKET NOZZLE COOLING nuclear-rocket regenerative-cooling analysis obtainable from NASA OTS price power of 46 probably be utilized propellant hydrogen range of reactor reactor power refractory wall coatings specific impulse square inch absolute system pressure drop system pressure ratio TECHNICAL NOTE D-482 techniques for improving thermal conductivity thermal radiation thin highly conductive TN D-482 National total heat flux turbopump utilized to achieve values of chamber values of system William H