Add to ORKGStatic tests of 65 inch diameter subscale rocket engines to evaluate nozzle fabrication methods, noz...
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle section
Cylindrical rocket thrust chamber cylinders were coated with a 0.203 mm (0.008 in.) layer of zirconi...
Protective coatings of refractory metals in rocket nozzles for liquid propellant
Testing thermal barrier coatings for flame surface of regeneratively cooled chamber operating with F...
Bipropellant rocket engines with radiation cooled thrust combustion chambers of molybdenum fired for...
Ceramic thermal protective coating system for regeneratively cooled hydrogen oxygen thrust chambe
Evaluation testing of protective coatings on refractory metals for nozzles and chamber
Thermal barrier coating for use on water cooled nozzle of solid propellant rocket engin
Hot firing tests with FLOX/methane propellants for evaluating pyrolytic refractory composite materia...
Protective coating of phosphate-bonded zirconia for regeneratively cooled thrust chamber
Feasibility of using ductile nickel-chromium alloy claddings to protect chromium alloy turbine vanes...
Several plasma-sprayed coating systems were evaluated for structural stability in hydrogen plasma an...
As part of its major investment in the area of advanced space transportation, NASA is developing new...
Oxidation resistance and high temperature tests of rhenium, tungsten, hafnium, and tantalum matrix c...
Static tests of 65 inch diameter subscale rocket engines to evaluate nozzle fabrication methods, noz...
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle section
Cylindrical rocket thrust chamber cylinders were coated with a 0.203 mm (0.008 in.) layer of zirconi...
Protective coatings of refractory metals in rocket nozzles for liquid propellant
Testing thermal barrier coatings for flame surface of regeneratively cooled chamber operating with F...
Bipropellant rocket engines with radiation cooled thrust combustion chambers of molybdenum fired for...
Ceramic thermal protective coating system for regeneratively cooled hydrogen oxygen thrust chambe
Evaluation testing of protective coatings on refractory metals for nozzles and chamber
Thermal barrier coating for use on water cooled nozzle of solid propellant rocket engin
Hot firing tests with FLOX/methane propellants for evaluating pyrolytic refractory composite materia...
Protective coating of phosphate-bonded zirconia for regeneratively cooled thrust chamber
Feasibility of using ductile nickel-chromium alloy claddings to protect chromium alloy turbine vanes...
Several plasma-sprayed coating systems were evaluated for structural stability in hydrogen plasma an...
As part of its major investment in the area of advanced space transportation, NASA is developing new...
Oxidation resistance and high temperature tests of rhenium, tungsten, hafnium, and tantalum matrix c...
Static tests of 65 inch diameter subscale rocket engines to evaluate nozzle fabrication methods, noz...
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle section
Cylindrical rocket thrust chamber cylinders were coated with a 0.203 mm (0.008 in.) layer of zirconi...