Add to ORKGInjector baffles for flame stability in combustion chambers using nitrogen tetroxide and hydrazine mixtur
The effect of elevated chamber pressure on combustion efficiency and heat transfer has been determin...
Since the 1960s hydrazine (N2H4) is the commonly used monopropellant for various space propulsion sy...
A new countermeasure against injection-coupled combustion instabilities in liquid propellant rocket ...
Stability effects of several injector face baffle configurations on screech in hydrogen-oxygen rocke
Experimental, and theoretical evaluations of acoustic liners for screech suppression in rocket engin...
Effects of injector face baffle configurations on screech in hydrogen-oxygen rocket engin
Propellant injection velocity effect on screech in 20,000 pound hydrogen-oxygen rocket engin
Dynamic stability and performance of injectors, rocket liners, and supersonic combustor
A method for temperature control of the combustion gases in the peripheral zone of a rocket combusto...
Analytical and computational techniques were developed to predict the stability behavior of liquid p...
An experimental investigation was conducted to learn more about how the specific details of a concen...
Experimental investigation of acoustic liners to suppress screech in hydrogen-oxygen engine
Increasing demands for higher afterburner performance have required operation at progressively highe...
Across the world several so-called green propellants for in-space and orbital propulsion are investi...
Injector-element physical size effect on mixing and combustion of nitrogen tetroxide-hydrazine prope...
The effect of elevated chamber pressure on combustion efficiency and heat transfer has been determin...
Since the 1960s hydrazine (N2H4) is the commonly used monopropellant for various space propulsion sy...
A new countermeasure against injection-coupled combustion instabilities in liquid propellant rocket ...
Stability effects of several injector face baffle configurations on screech in hydrogen-oxygen rocke
Experimental, and theoretical evaluations of acoustic liners for screech suppression in rocket engin...
Effects of injector face baffle configurations on screech in hydrogen-oxygen rocket engin
Propellant injection velocity effect on screech in 20,000 pound hydrogen-oxygen rocket engin
Dynamic stability and performance of injectors, rocket liners, and supersonic combustor
A method for temperature control of the combustion gases in the peripheral zone of a rocket combusto...
Analytical and computational techniques were developed to predict the stability behavior of liquid p...
An experimental investigation was conducted to learn more about how the specific details of a concen...
Experimental investigation of acoustic liners to suppress screech in hydrogen-oxygen engine
Increasing demands for higher afterburner performance have required operation at progressively highe...
Across the world several so-called green propellants for in-space and orbital propulsion are investi...
Injector-element physical size effect on mixing and combustion of nitrogen tetroxide-hydrazine prope...
The effect of elevated chamber pressure on combustion efficiency and heat transfer has been determin...
Since the 1960s hydrazine (N2H4) is the commonly used monopropellant for various space propulsion sy...
A new countermeasure against injection-coupled combustion instabilities in liquid propellant rocket ...