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annular fuel annular stream brazed bustion calibration Chamber Length chamber pressures characteristic length combustion chamber combustion-chamber combustor Contraction ratio Cooling-water flow engine was principally erosion expansion ratio fabrication formed by welding FUEL AND LIQUID fuel combination fuel jets fuel stream full face area full-scale engines glow plug high-performance holes hypodermic tubes igniter injection injector face injector head jet diameter JP-4 and Liquid JP-4 fuel l/2-percent-beryllium copper l0 percent l5 minutes lb/sq Lewis Research Center liquid fuel liquid oxygen liquid-oxygen streams main propellant mass mean drop missile and space-vehicle NACA RM nozzle Oxidant-fuel oxygen and JP-4 Performance of JP-4 pounds per square pressure drop principally due propellant flow ribs rocket engines sea-level conditions shown in figure shutdown soft brass mandrel space-vehicle boosters spark plug specific impulse square inch surrounding the oxidant thermocouple thrust type of construction vacuum furnace Vearl wall thickness Weight flow wind-tunnel