Add to ORKGImproved injector for oxygen difluoride and diborane has better mixing characteristics and is able to project fuel onto the wall of the combustion chamber for better cooling. It produces an essentially conical, diverging, continuous sheet of propellant mixture formed by similarly shaped and continuously impinging sheets of fuel and oxidant
As part of the Combustion Stability Tool Development project funded by the Air Force Space and Missi...
The Air Force Research Laboratory (AFRL) is undertaking a program to improve the development of a ga...
An evaluation of an existing analytical heat transfer model was made to develop the technology of bo...
Injector manifold assembly for bipropellant rocket engines providing for fuel propellant to serve as...
Liquid propellant rocket engine injectors using coaxial elements where the center liquid is swirled ...
Chamber technology for space storable propellant combinations featuring oxygen difluorid
A high number of liquid oxygen and gaseous hydrogen orifices per unit area are provided in an inject...
A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector ...
An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical do...
A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine...
abstract: Atomization of fluids inside combustion chamber has been a very complex and long-lasting s...
Porous injectors represent an alternative injection concept to coaxial injectors for rocket engine a...
Injector design criteria are provided for gaseous hydrogen-gaseous oxygen propellants. Design equati...
Reaction engine operates on the principle of a controlled condensed detonation. In this engine the g...
An experimental program was conducted to characterize the circular coaxial injector concept for appl...
As part of the Combustion Stability Tool Development project funded by the Air Force Space and Missi...
The Air Force Research Laboratory (AFRL) is undertaking a program to improve the development of a ga...
An evaluation of an existing analytical heat transfer model was made to develop the technology of bo...
Injector manifold assembly for bipropellant rocket engines providing for fuel propellant to serve as...
Liquid propellant rocket engine injectors using coaxial elements where the center liquid is swirled ...
Chamber technology for space storable propellant combinations featuring oxygen difluorid
A high number of liquid oxygen and gaseous hydrogen orifices per unit area are provided in an inject...
A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector ...
An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical do...
A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine...
abstract: Atomization of fluids inside combustion chamber has been a very complex and long-lasting s...
Porous injectors represent an alternative injection concept to coaxial injectors for rocket engine a...
Injector design criteria are provided for gaseous hydrogen-gaseous oxygen propellants. Design equati...
Reaction engine operates on the principle of a controlled condensed detonation. In this engine the g...
An experimental program was conducted to characterize the circular coaxial injector concept for appl...
As part of the Combustion Stability Tool Development project funded by the Air Force Space and Missi...
The Air Force Research Laboratory (AFRL) is undertaking a program to improve the development of a ga...
An evaluation of an existing analytical heat transfer model was made to develop the technology of bo...