Add to ORKGDetermination of combustion stability limits with hydrogen-oxygen combustor of variable lengt
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle section
Characteristic velocities of six single-element injectors that separately varied propellant spreadin...
Coaxial injector thrust effects on combustion stability of hydrogen-oxygen rocket engin
Chamber pressure, contraction ratio, and flow per element effects on acoustic mode instability in hy...
An experimental investigation was conducted to determine what arrangement of film-coolant-injection ...
An experimental investigation was conducted to learn more about how the specific details of a concen...
Propellant injection velocity effect on screech in 20,000 pound hydrogen-oxygen rocket engin
Injector radial distribution and thrust chamber geometry effect on acoustic mode instability in hydr...
Test firing evaluation of six ablative-material thrust chambers as components of storable propellant...
An experimental investigation was conducted to develop a high-thrust, high-performance, concentric t...
The combustion stability characteristics of a combustor consisting of a single shear element and a c...
Liquid oxygen set behavior during combustion instability in gaseous hydrogen fueled rocket combusto
Rocket engines achieve extraordinary high energy densities within the chamber in the form of high pr...
Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hyd...
Determination of combustion stability limits with hydrogen-oxygen combustor of variable lengt
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle section
Characteristic velocities of six single-element injectors that separately varied propellant spreadin...
Coaxial injector thrust effects on combustion stability of hydrogen-oxygen rocket engin
Chamber pressure, contraction ratio, and flow per element effects on acoustic mode instability in hy...
An experimental investigation was conducted to determine what arrangement of film-coolant-injection ...
An experimental investigation was conducted to learn more about how the specific details of a concen...
Propellant injection velocity effect on screech in 20,000 pound hydrogen-oxygen rocket engin
Injector radial distribution and thrust chamber geometry effect on acoustic mode instability in hydr...
Test firing evaluation of six ablative-material thrust chambers as components of storable propellant...
An experimental investigation was conducted to develop a high-thrust, high-performance, concentric t...
The combustion stability characteristics of a combustor consisting of a single shear element and a c...
Liquid oxygen set behavior during combustion instability in gaseous hydrogen fueled rocket combusto
Rocket engines achieve extraordinary high energy densities within the chamber in the form of high pr...
Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hyd...
Determination of combustion stability limits with hydrogen-oxygen combustor of variable lengt
Evaluation and erosion of nonmetallic ablating materials as rocket nozzle section
Characteristic velocities of six single-element injectors that separately varied propellant spreadin...