Add to ORKGLiquid propellant rocket engine throttling injector design based on exhaust gas counter flow and heat transfer for inflowing propellant vaporization and combustion stability test
Apparatus, techniques, and instrumentation for experimental correlation of nonreactive injection sch...
Boundary flow composition in rocket motor combustion chamber with exhaust system samplin
A platelet face injector for the Orbit Maneuvering Engine (OME) on the space shuttle was evaluated a...
Evaluation of throttling injector concepts applicable to advanced cryogenic engine
Injector design criteria are provided for gaseous hydrogen-gaseous oxygen propellants. Design equati...
Operating characteristics and design aspects of injector, combustion chamber, and exhaust nozzle for...
The previous 'Art of Injector Design' is maturing and merging with the more systematic 'Science of C...
A summary of the design analyses for a liquid rocket injector using oxygen and RP-1 propellants at h...
The performance and stability of liquid rocket engines is determined to a large degree by atomizatio...
The Air Force Research Laboratory (AFRL) is undertaking a program to improve the development of a ga...
The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydroge...
The application of heat pipe technology to the design of rocket engine thrust chambers is discussed....
NASA is developing the Space Launch System (SLS) for crewed exploration missions beyond low Earth or...
A computer program for analyzing rocket engine performance was developed. The program is concerned w...
An experimental program was conducted to characterize the circular coaxial injector concept for appl...
Apparatus, techniques, and instrumentation for experimental correlation of nonreactive injection sch...
Boundary flow composition in rocket motor combustion chamber with exhaust system samplin
A platelet face injector for the Orbit Maneuvering Engine (OME) on the space shuttle was evaluated a...
Evaluation of throttling injector concepts applicable to advanced cryogenic engine
Injector design criteria are provided for gaseous hydrogen-gaseous oxygen propellants. Design equati...
Operating characteristics and design aspects of injector, combustion chamber, and exhaust nozzle for...
The previous 'Art of Injector Design' is maturing and merging with the more systematic 'Science of C...
A summary of the design analyses for a liquid rocket injector using oxygen and RP-1 propellants at h...
The performance and stability of liquid rocket engines is determined to a large degree by atomizatio...
The Air Force Research Laboratory (AFRL) is undertaking a program to improve the development of a ga...
The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydroge...
The application of heat pipe technology to the design of rocket engine thrust chambers is discussed....
NASA is developing the Space Launch System (SLS) for crewed exploration missions beyond low Earth or...
A computer program for analyzing rocket engine performance was developed. The program is concerned w...
An experimental program was conducted to characterize the circular coaxial injector concept for appl...
Apparatus, techniques, and instrumentation for experimental correlation of nonreactive injection sch...
Boundary flow composition in rocket motor combustion chamber with exhaust system samplin
A platelet face injector for the Orbit Maneuvering Engine (OME) on the space shuttle was evaluated a...