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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